CN114280217A - Aviation fuel oil automatic ignition experimental device and experimental method thereof - Google Patents
Aviation fuel oil automatic ignition experimental device and experimental method thereof Download PDFInfo
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- CN114280217A CN114280217A CN202111598692.0A CN202111598692A CN114280217A CN 114280217 A CN114280217 A CN 114280217A CN 202111598692 A CN202111598692 A CN 202111598692A CN 114280217 A CN114280217 A CN 114280217A
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- 238000002474 experimental method Methods 0.000 title claims abstract description 92
- 239000000295 fuel oil Substances 0.000 title claims abstract description 88
- 239000000446 fuel Substances 0.000 claims abstract description 187
- 239000003921 oil Substances 0.000 claims abstract description 138
- 238000002485 combustion reaction Methods 0.000 claims abstract description 73
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims description 107
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims description 105
- 239000001301 oxygen Substances 0.000 claims description 105
- 229910052760 oxygen Inorganic materials 0.000 claims description 105
- 229910052757 nitrogen Inorganic materials 0.000 claims description 52
- 238000006243 chemical reaction Methods 0.000 claims description 45
- 239000002828 fuel tank Substances 0.000 claims description 28
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 claims description 23
- 239000003546 flue gas Substances 0.000 claims description 23
- 239000007789 gas Substances 0.000 claims description 21
- 238000005070 sampling Methods 0.000 claims description 20
- 238000002347 injection Methods 0.000 claims description 19
- 239000007924 injection Substances 0.000 claims description 19
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 17
- 239000000523 sample Substances 0.000 claims description 16
- 230000001502 supplementing effect Effects 0.000 claims description 15
- 238000010438 heat treatment Methods 0.000 claims description 13
- 239000007921 spray Substances 0.000 claims description 13
- 239000007788 liquid Substances 0.000 claims description 12
- 238000001514 detection method Methods 0.000 claims description 11
- 239000007791 liquid phase Substances 0.000 claims description 10
- 238000004891 communication Methods 0.000 claims description 9
- 239000012071 phase Substances 0.000 claims description 9
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Abstract
The invention discloses an aviation fuel automatic ignition experimental device and an experimental method thereof. The ignition experimental device comprises an oil supply system, an ignition experimental system and a communicating assembly. The oil supply system comprises a frame, an oil tank, a stop valve, an aviation fuel pump, a first electromagnetic valve, a safety valve and an electric pressure reducing valve, the communicating assembly comprises the first valve and a second valve, and the ignition experiment system comprises a combustion chamber, a second electromagnetic valve, a third electromagnetic valve and a high-energy igniter. The combustion chamber comprises an oil nozzle and an ignition rod. The ignition experiment system can realize the separation of the oil supply system and the ignition experiment system, can reduce the possibility of detonation of the ignition experiment system to the oil supply system, enables ignition experiments to be safer, and can be arranged in various experiment environments according to requirements to meet various experiment requirements. Meanwhile, the invention can fully burn the fuel oil, avoid excessive fuel oil loss in the combustion chamber, make the experimental oil quantity easier to control, improve the combustion efficiency of the fuel oil and improve the experimental precision.
Description
Technical Field
The invention relates to an experimental device in the technical field of aviation fuel ignition experiments, in particular to an aviation fuel automatic ignition experimental device and an aviation fuel automatic ignition experimental method of the experimental device.
Background
Aviation fuel refers to a fuel variety specifically designed for aircraft, and has a higher quality than fuel used in heating systems and automobiles, and generally contains different additives to reduce the risk of icing and explosion due to high temperature. Aviation fuel oil is divided into two main categories: aviation gasoline is used for reciprocating engine airplane. Aviation kerosene is used in aviation gas turbine engines and ramjet engines. The aviation fuel oil processing equipment is mainly an aviation piston engine. The aviation piston engine has the same working principle as that of a common automobile engine, but has large power and light dead weight, so that the quality requirement on aviation gasoline is similar to that of automobile gasoline.
Some advanced large passenger aircraft can fly at high altitude over 1 ten thousand meters, and the ignition of the engine of the aircraft must adapt to the severe conditions of high altitude oxygen deficiency and low air temperature and air pressure. Therefore, the aviation fuel needs to be tested by a special ignition test device, and whether the combustion effect of the fuel reaches the actually required effect or not is judged. However, the existing aviation fuel ignition experimental device has the problems of insufficient combustion and uncontrollable oil quantity.
Disclosure of Invention
The invention provides an aviation fuel oil automatic ignition experimental device and an experimental method thereof, aiming at solving the technical problems of insufficient combustion and uncontrollable oil quantity of the existing aviation fuel oil ignition experimental device.
The invention is realized by adopting the following technical scheme: an aviation fuel automatic ignition experimental device comprises an oil supply system, an ignition experimental system and a communication assembly;
the oil supply system comprises a frame, an oil tank, a stop valve, an aviation fuel pump, a first electromagnetic valve, a safety valve and an electric pressure reducing valve; the fuel tank is arranged in the frame, is provided with at least one oil outlet end and at least one oil inlet end, and is used for storing fuel oil; the feed end of the stop valve is communicated with the oil outlet end of the oil tank, and the discharge end of the stop valve is communicated with the oil inlet end of the aviation fuel pump; the feed ends of the electromagnetic valve I, the safety valve and the electric pressure reducing valve are all communicated with the oil outlet end of the aviation fuel pump, and the discharge ends are all communicated with the oil inlet end of the oil tank;
the communication assembly comprises a first valve and a second valve; one end of the first valve is communicated with the oil outlet end of the aviation fuel pump; one end of the second valve is communicated with the first electromagnetic valve, the safety valve and the discharge end of the electric pressure reducing valve;
the ignition experiment system comprises a combustion chamber, a second electromagnetic valve, a third electromagnetic valve and a high-energy igniter; the combustion chamber comprises an oil nozzle and an ignition rod; the oil nozzle is communicated with the other end of the first valve through a second electromagnetic valve, and one end of the ignition rod is positioned in an oil nozzle of the oil nozzle; the high-energy igniter is connected with the other end of the ignition rod and enables the ignition rod to generate sparks in the fuel injection port so as to ignite fuel injected from the fuel injection port; and two ends of the electromagnetic valve III are respectively communicated with the other end of the valve II and the oil spray nozzle.
The fuel oil supply system performs experiments through the fuel supply system, the communication assembly and the ignition experiment system, fuel oil in a fuel tank in the fuel supply system can be output to the first electromagnetic valve, the safety valve and the electric pressure reducing valve through the aviation fuel pump and further returned to the fuel tank, the fuel oil can be fully mixed, the fuel oil can enter the ignition experiment system through the first valve and can be sprayed out of a fuel injection port under the control action of the second electromagnetic valve, the sprayed oil quantity is controllable, so that the high-energy igniter can drive the ignition rod to generate ignition flowers to ignite the fuel oil, meanwhile, redundant fuel oil in a combustion chamber can be returned to the fuel tank through the second valve, the fuel oil can be fully combusted, and in the process of adjusting the fuel oil quantity, when the opening degree of the second electromagnetic valve is small, the safety valve and the electric pressure reducing valve in the fuel supply system can play a buffering role, and the problems that the existing aviation fuel oil ignition experiment device is insufficient in combustion and the prior art are solved, The uncontrollable technical problem of oil mass has obtained the burning fully, the oil mass is controllable, the high technological effect of experimental precision.
As a further improvement of the above scheme, the combustion chamber further comprises a reaction chamber, a vacuum gauge and a plurality of windows; the reaction chamber is of a closed structure, and the oil nozzle and the ignition rod are both arranged in the reaction chamber; the vacuum gauge is used for detecting and displaying the vacuum degree in the reaction chamber; the window is installed on the reaction chamber and is used for external personnel to observe the combustion condition in the reaction chamber.
As a further improvement of the above scheme, the ignition experimental system further comprises a second pressure gauge, a temperature sensor and a pressure transmitter; the pressure gauge II is used for displaying the pressure of the fuel oil conveyed from the valve I to the electromagnetic valve II; the temperature sensor is used for detecting the temperature of the fuel conveyed from the first valve to the second solenoid valve; and the pressure transmitter is used for converting the pressure of the fuel oil conveyed to the electromagnetic valve II by the valve I into an electric signal.
As a further improvement of the above scheme, the oil supply system further comprises an oil flow meter and a first pressure gauge; the fuel flow meter is used for displaying the flow of the fuel flowing out of the aviation fuel pump; and the pressure gauge is used for displaying the pressure of the fuel flowing out of the aviation fuel pump.
As a further improvement of the above scheme, the oil supply system further comprises a heating controller and an electromagnetic heater; the electromagnetic heater is arranged in the oil tank and is used for heating fuel oil in the oil tank; the electromagnetic heater is used for turning on or off the electromagnetic heater, and the temperature of the fuel in the fuel tank is kept within a preset fuel temperature range.
Further, the reaction chamber has at least one gas inlet through which oxygen enters; the ignition experiment system also comprises an oxygen inlet pipe, an oxygen flow controller and an oxygen supplementing valve; the oxygen inlet pipe is connected with the air inlet and is used for conveying oxygen to the air inlet; the oxygen supplementing valve is arranged on the oxygen inlet pipe and is used for opening or closing the oxygen inlet pipe; the oxygen flow controller is installed on the oxygen inlet pipe and is used for adjusting the amount of oxygen entering the air inlet.
As a further improvement of the above scheme, the ignition experimental system further comprises a flue gas processor, a roots blower, a low-pressure buffer tank, a water ring pump, an air flow controller and an air make-up valve; the flue gas processor is used for processing the flue gas generated in the combustion chamber and conveying the flue gas to the low-pressure buffer tank through the Roots blower; the low-pressure buffer tank is used for buffering the flue gas treated by the flue gas processor and outputting the flue gas through the water ring pump; the air flow controller is used for adjusting the flow of the air which is supplemented into the low-pressure buffer tank by the air supplementing valve.
Further, the reaction chamber has at least one inlet for nitrogen; the ignition experiment system also comprises a nitrogen inlet pipe, a nitrogen flow controller and a nitrogen supplementing valve; the nitrogen inlet pipe is connected with the gas inlet and is used for conveying nitrogen to the gas inlet; the nitrogen supplementing valve is arranged on the nitrogen inlet pipe and is used for opening or closing the nitrogen inlet pipe; the nitrogen flow controller is installed on the nitrogen inlet pipe and is used for adjusting the amount of nitrogen entering the air inlet.
As a further improvement of the above scheme, the oil nozzle is of a slit structure; the ignition experiment system also comprises a gas phase sampling tube, a valve III, an oxygen detecting tube, an oxygen probe, a valve IV, a dissolved oxygen detecting tube, a valve V, a dissolved oxygen analyzer, a nitrogen detecting tube, a valve VI, a liquid phase sampling tube, a valve VII, a blow-off tube, a valve VIII and a vibration table; the gas-phase sampling pipe is communicated with the combustion chamber, and the third valve is used for opening or closing the gas-phase sampling pipe; the oxygen detecting pipe is communicated with the combustion chamber, the oxygen probe is used for detecting the oxygen concentration of the gas output from the oxygen detecting pipe, and the valve IV is used for opening or closing the oxygen detecting pipe; the dissolved oxygen detecting tube is communicated with the combustion chamber, the dissolved oxygen analyzer is used for analyzing the dissolved oxygen content of gas flowing out of the dissolved oxygen detecting tube, and the valve five is used for opening or closing the dissolved oxygen detecting tube; the nitrogen detection pipe is communicated with the combustion chamber, and the sixth valve is used for opening or closing the nitrogen detection pipe; the liquid phase sampling pipe is used for extracting liquid in the combustion chamber, and the valve seventh is used for opening or closing the liquid phase sampling pipe; the blow-off pipe is communicated with the combustion chamber and is used for discharging waste liquid generated by combustion in the combustion chamber; the valve eight is used for opening or closing the sewage discharge pipe; the vibration table is used for vibrating the combustion chamber, so that fuel oil on the slit structure is uniformly distributed.
The invention also provides an aviation fuel oil automatic ignition experimental method which is applied to any aviation fuel oil automatic ignition experimental device and comprises the following steps:
(1) storing fuel oil into the fuel tank, and starting the aviation fuel pump to enable the fuel oil in the fuel tank to pass through the first electromagnetic valve, the safety valve and the electric pressure reducing valve and return to the fuel tank;
(2) opening the first valve to enable fuel output from the aviation fuel pump to be conveyed to the second electromagnetic valve;
(3) opening the second electromagnetic valve to enable the fuel to be sprayed out from the fuel spray opening of the fuel spray nozzle;
(4) opening the electromagnetic valve III to enable part of the fuel oil reaching the fuel spray nozzle to flow back to the fuel tank;
(5) adjusting the opening degree of the first electromagnetic valve, the second electromagnetic valve and the third electromagnetic valve to enable the fuel quantity sprayed from the fuel injection port to reach a preset fuel quantity;
(6) and driving one end of the ignition rod to generate an ignition flower through the high-energy igniter so as to ignite the fuel at the fuel injection port.
Compared with the conventional aviation fuel oil ignition experimental device, the aviation fuel oil automatic ignition experimental device and the experimental method thereof have the following beneficial effects:
1. this aviation fuel oil auto-ignition experimental apparatus, it passes through oil feeding system, UNICOM's subassembly and ignition experimental system experiment, can realize oil feeding system and ignition experimental system's separation, distance between the two can be very far away, therefore can reduce the possibility that ignition experimental system led to the fact detonation to oil feeding system, especially can produce the high temperature situation at the experiment in-process of lighting up, can keep apart oil feeding system high temperature experiment environment, it is safer to make the experiment of lighting up, and the experiment system of lighting up can set up in various experimental environment as required, thereby satisfy various experiment demands.
2. This aviation fuel oil auto-ignition experimental apparatus, the fuel oil that the aviation experiment was used can be stored to the oil tank among its oil feeding system, the aviation fuel pump can be further exported the fuel oil of storage, and the stop valve is then as the master switch of fuel oil output, can adjust the total outflow of fuel oil output, solenoid valve one simultaneously, relief valve and electronic relief pressure valve can return the part of aviation fuel oil pump output or whole fuel oil to the oil tank in, just so can guarantee when not experimenting, whole oil feeding system still is in endless in-process, can make each composition misce bene in the fuel oil, make the fuel oil similar with the aviation fuel's of practical use service environment in the oil tank, thereby improve the experiment precision of igniteing. In addition, the electric pressure reducing valve can also be used as a pressure regulating structure, so that oil liquid pre-returned to the oil tank can be prevented from flowing back to the output side of the aviation fuel pump, and the normal circulation of the fuel oil is ensured.
3. This aviation fuel oil autoignition experimental apparatus, the back is switched on to the valve one of its UNICOM subassembly, and the fuel of aviation fuel pump output can enter into the experiment system of lighting a fire, through manometer two, temperature sensor and pressure transmitter detect the back, reachs the feed liquor end of solenoid valve two, and solenoid valve two can export the fuel to the fuel sprayer, and then from the nozzle blowout, high energy point firearm just can order about the firing bar like this and produce the ignition flower in order to light the fuel to the experiment is lighted in the realization. Meanwhile, redundant fuel in the combustion chamber can return to the fuel tank through the electromagnetic valve III and the valve II, so that the fuel can be fully combusted, excessive fuel loss in the combustion chamber is avoided, and in the process of adjusting the fuel quantity, when the opening degree of the electromagnetic valve II is small, a safety valve and an electric pressure reducing valve in the oil supply system can play a buffering role, the oil pressure in an ignition experiment system can be reduced, the experimental fuel quantity is more easily controlled, the combustion efficiency of the fuel is improved, and the experiment precision is further improved.
4. This aviation fuel auto-ignition experimental apparatus still can set up reaction chamber, vacuometer and a plurality of window in the combustion chamber among its ignition experimental system, like this after the evacuation, can master the vacuum condition in the reaction chamber in real time through the vacuometer, can observe the combustion condition in the reaction chamber through the window moreover to in the experiment of igniteing. Moreover, the ignition experimental device can also be provided with a heating controller and an electromagnetic heater, the heating controller can control the electromagnetic heater to heat, so that the temperature of fuel in the fuel tank is always within a preset fuel temperature range, the temperature of actual fuel is simulated, and the experiment is closer to an actual scene.
5. This aviation fuel oil auto-ignition experimental apparatus, its ignition experimental system still can set up into oxygen pipe, oxygen flow controller and oxygenating valve, these structures can provide oxygen for the reacting chamber, make the experiment normally go on, still can set up oxygen detecting tube and oxygen probe simultaneously, just so can survey the oxygen content in the combustion chamber in real time, make flow controller control oxygenating valve supply, thereby oxygen content can be in any experiment concentration region in making the combustion chamber, be favorable to going on of experiment, simulate out the sight of carrying out the experiment in the condition of high altitude hypoxemia simultaneously.
The beneficial effects of the aviation fuel oil automatic ignition experimental method are the same as those of the ignition experimental device, and are not repeated herein.
Drawings
FIG. 1 is a system block diagram of an aviation fuel automatic ignition experimental device in embodiment 1 of the invention;
FIG. 2 is a schematic partial structural diagram of the aviation fuel automatic ignition experimental device shown in FIG. 1;
FIG. 3 is a schematic partial structural view of an aviation fuel oil automatic ignition experimental device according to embodiment 2 of the invention;
FIG. 4 is a system block diagram of the aviation fuel automatic ignition experimental device shown in FIG. 3;
fig. 5 is a system block diagram of an aviation fuel automatic ignition experimental apparatus according to embodiment 3 of the present invention.
Description of the symbols:
1 frame 29 low pressure buffer tank
2 oil tank 30 water ring pump
3 stop valve 31 air flow controller
4 aviation fuel pump 32 air compensating valve
5 magnetic valve-33 reaction chamber
6 safety valve 34 vacuum gauge
7 electric pressure reducing valve 35 window
8 oil flowmeter 37 nitrogen flow controller
9-pressure meter-38 nitrogen supplementing valve
10 blowoff valve 40 valve three
11 heating controller 42 oxygen probe
12 electromagnetic heater 43 valve four
13 valves, 45 valves, five
14-valve-II 46 dissolved oxygen analyzer
15 combustion chamber 48 valve six
16 solenoid valve two 50 valve seven
17 solenoid valve three 52 valve eight
18 high-energy igniter 53 shaking table
19 pressure gauge two 54 electromagnetic valve four
20 temperature sensor 55 valve nine
21 pressure transmitter 56 filter one
22 oil nozzle 57 cold-hot device
23 ignition rod 58 filter two
25 oxygen flow controller 59 valve ten
26 oxygen supply valve 60 electromagnetic valve five
27 flue gas treater 61 water pump
28 Roots blower 62 temperature control pipe
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
Example 1
Referring to fig. 1 and fig. 2, the embodiment provides an aviation fuel automatic ignition experimental apparatus, which is used for carrying out an automatic ignition experiment on aviation fuel and can simulate an ignition effect of the fuel in different aviation environments. The aviation fuel oil automatic ignition experimental device comprises an oil supply system, an ignition experimental system and a communicating assembly. Because oil feeding system links to each other with the experiment system of igniteing through the UNICOM subassembly, can realize oil feeding system and the separation of ignition experiment system, and distance between the two can be very far away, therefore can reduce the possibility that the experiment system of igniteing led to the fact detonation to oil feeding system, especially can produce the high temperature situation at the experiment in-process of igniteing, can keep apart oil feeding system high temperature experiment environment, it is safer to make the experiment of igniteing, and the experiment system of igniteing can set up in various experimental environment as required, thereby satisfy various experiment demands.
It should be noted that, in this embodiment, the communication between the structures may be performed through a pipeline, or may be performed directly, or of course, other structures may be employed for the communication, and for convenience of description, the description of the communication structure will be omitted in the following description. When the pipeline is adopted to communicate all parts, the pipeline can adopt an oil pipe, particularly an oil pipe for actual aviation as a communicating structure for use, and oil-resistant material heat-insulating materials can be laid on the inner wall of the pipeline, so that the normal operation of an experiment is ensured.
The oil supply system comprises a frame 1, an oil tank 2, a stop valve 3, an aviation fuel pump 4, a first electromagnetic valve 5, a safety valve 6 and an electric pressure reducing valve 7, and in the embodiment, the oil supply system also comprises an oil flow meter 8, a first pressure gauge 9, a blow-down valve 10, a heating controller 11 and an electromagnetic heater 12. The frame 1 may be designed into various sizes of frames according to actual needs, which may be formed by connecting a plurality of frame columns in sequence, and in some embodiments, the frame 1 may be a structure capable of moving automatically, which is capable of moving on the ground. The fuel tank 2 is installed in the frame 1, has at least one fuel outlet end and at least one fuel inlet end, and stores fuel. Wherein the oil outlet end is arranged at the bottom of the oil tank 2, and the oil inlet end is arranged at the top of the oil tank 2, so that when the fuel circulates, the fuel can return to the oil tank 2 again from the top under the action of gravity, and the output fuel can be pressed out under the action of oil pressure. The stop valve 3 is close to the oil outlet end of the oil tank 2, the feeding end is communicated with the oil outlet end of the oil tank 2, and the discharging end is communicated with the oil inlet end of the aviation fuel pump 4. The stop valve 3 is used as a master switch of fuel output, and can adjust the total output of the fuel output. The feeding ends of the first electromagnetic valve 5, the safety valve 6 and the electric pressure reducing valve 7 are communicated with the oil outlet end of the aviation fuel pump 4, and the discharging end is communicated with the oil inlet end of the oil tank 2. Because the first electromagnetic valve 5, the safety valve 6 and the electric pressure reducing valve 7 can return part or all of fuel output by the aviation fuel pump 4 to the fuel tank 2, the whole fuel supply system is still in a circulating process when an experiment is not carried out, all components in the fuel can be uniformly mixed, the fuel in the fuel tank 2 is similar to the actual aviation fuel using environment, and the ignition experiment precision is improved. In addition, the electric pressure reducing valve 7 can also be used as a pressure regulating structure, so that oil liquid which is pre-returned to the oil tank 2 can be prevented from flowing back to the output side of the aviation fuel pump 4, and the normal circulation of the fuel oil is ensured.
In the present embodiment, the fuel flow meter 8 is used to display the flow rate of fuel flowing from the aircraft fuel pump 4. The first pressure gauge 9 is used for displaying the pressure of the fuel flowing out of the aviation fuel pump 4. The blow-off valve 10 is used to discharge oily waste from the oil tank 2. An electromagnetic heater 12 is installed in the fuel tank 2 and serves to heat the fuel located in the fuel tank 2. The electromagnetic heater 12 is used to turn on or off the electromagnetic heater 12, and the temperature of the fuel in the fuel tank 2 is maintained within a preset fuel temperature range. Like this, heating controller 11 can control electromagnetic heater 12 and heat, makes fuel temperature be located predetermineeing fuel temperature range in the oil tank 2 all the time to simulate out the temperature of actual fuel, make the experiment more be close to actual scene.
The communicating component comprises a first valve 13 and a second valve 14, and in other embodiments, the communicating component further comprises a plurality of oil pipes for communicating the oil supply system and the ignition experiment system. Wherein, one end of the first valve 13 is communicated with the oil outlet end of the aviation fuel pump 4. One end of the second valve 14 is communicated with the first electromagnetic valve 5, the safety valve 6 and the discharge end of the electric pressure reducing valve 7. The first valve 13 and the second valve 14 can be hand valves, and a user can manually adjust the first valve 13 and the second valve 14, so that the oil supply system and the ignition experiment system are switched on and off.
The ignition experiment system comprises a combustion chamber 15, a second electromagnetic valve 16, a third electromagnetic valve 17 and a high-energy igniter 18, and in the embodiment, the ignition experiment system further comprises a second pressure gauge 19, a temperature sensor 20 and a pressure transmitter 21. The combustion chamber 15 comprises an oil nozzle 22 and an ignition rod 23, and can provide a closed experimental site for ignition. The oil nozzle 22 is communicated with the other end of the first valve 13 through the second electromagnetic valve 16, and one end of the ignition rod 23 is positioned in an oil nozzle of the oil nozzle 22. The high-energy igniter 18 is connected to the other end of the ignition rod 23 and causes the ignition rod 23 to generate a spark in the fuel injection port to ignite the fuel injected from the fuel injection port. Two ends of the electromagnetic valve III 17 are respectively communicated with the other end of the valve II 14 and the oil nozzle 22. In the present embodiment, the oil nozzle 22 is a slit structure, and the oil nozzle is a slit in the slit structure. After the fuel has been sprayed, the fuel will be present in the slit, and the flame thus ignited will burn on the slit, while the remaining fuel will flow further through the slit to the solenoid valve three 17 and back into the fuel tank 2. The second pressure gauge 19 is installed between the first valve 13 and the second solenoid valve 16, and is used for displaying the pressure of the fuel delivered from the first valve 13 to the second solenoid valve 16. The temperature sensor 20 is installed between the first valve 13 and the second solenoid valve 16, and is used to detect the temperature of the fuel delivered from the first valve 13 to the second solenoid valve 16. The pressure transmitter 21 is installed between the first valve 13 and the second solenoid valve 16, and is used to convert the pressure of the fuel delivered from the first valve 13 to the second solenoid valve 16 into an electrical signal. The second pressure gauge 19, the temperature sensor 20 and the pressure transmitter 21 should be as close as possible to the vicinity of the fuel injection nozzle 22 to detect the fuel injected from the fuel injection nozzle 22.
After the first valve 13 is switched on, the fuel output by the aviation fuel pump 4 enters an ignition experiment system, and after the fuel is detected by the second pressure gauge 19, the temperature sensor 20 and the pressure transmitter 21, the oil pressure and the temperature can be detected in real time, so that experimenters can conveniently master the input parameters of the fuel in time to perform experiment recording. The fuel then reaches the inlet of the second solenoid valve 16, and the second solenoid valve 16 can deliver the fuel to the injection nozzle 22, while the second solenoid valve 16 can regulate the quantity of fuel delivered to the injection nozzle 22, and therefore the quantity of fuel ignited. Subsequently, the fuel is sprayed from the fuel injection port, so that the high-energy igniter 18 can drive the ignition rod 23 to generate ignition spark to ignite the fuel, thereby realizing an ignition experiment and ensuring that the ignited fuel is the fuel required by the experiment. Meanwhile, redundant fuel oil in the combustion chamber 15 can return to the oil tank 2 through the electromagnetic valve III 17 and the valve II 14, so that the fuel oil can be fully combusted, excessive fuel oil loss in the combustion chamber 15 is avoided, and in the process of adjusting the fuel oil quantity, when the opening degree of the electromagnetic valve II 16 is small, the safety valve 6 and the electric pressure reducing valve 7 in the oil supply system can play a buffering role, the oil pressure in an ignition experiment system can be reduced, the experimental oil quantity is controlled more easily, the combustion efficiency of the fuel oil is improved, and the experiment precision is further improved.
To sum up, compare in current ignition experimental apparatus, the aviation fuel auto-ignition experimental apparatus of this embodiment has following beneficial effect:
1. this aviation fuel oil auto-ignition experimental apparatus, it passes through oil feeding system, UNICOM's subassembly and ignition experimental system experiment, can realize oil feeding system and ignition experimental system's separation, distance between the two can be very far away, therefore can reduce the possibility that ignition experimental system led to the fact detonation to oil feeding system, especially can produce the high temperature situation at the experiment in-process of lighting up, can keep apart oil feeding system high temperature experiment environment, it is safer to make the experiment of lighting up, and the experiment system of lighting up can set up in various experimental environment as required, thereby satisfy various experiment demands.
2. This aviation fuel oil automatic ignition experimental apparatus, fuel oil that the aviation experiment was used can be stored to oil tank 2 among its oil feeding system, aviation fuel pump 4 can be further exported the fuel of storage, and stop valve 3 then is as the master switch of fuel output, can adjust the total output of fuel output, solenoid valve 5 simultaneously, relief valve 6 and electronic relief pressure valve 7 can return the part of aviation fuel pump 4 output or whole fuel to in oil tank 2, just so can guarantee when not experimenting, whole oil feeding system still is in the endless in-process, can make each composition misce bene in the fuel, make fuel oil in the oil tank 2 similar with the aviation fuel's of practical use service environment, thereby improve the experiment precision of igniteing. In addition, the electric pressure reducing valve 7 can also be used as a pressure regulating structure, so that oil liquid which is pre-returned to the oil tank 2 can be prevented from flowing back to the output side of the aviation fuel pump 4, and the normal circulation of the fuel oil is ensured.
3. According to the aviation fuel oil automatic ignition experimental device, after the first valve 13 of the communicating component is conducted, fuel oil output by the aviation fuel oil pump 4 can enter an ignition experimental system, and after the fuel oil is detected by the second pressure gauge 19, the second temperature sensor 20 and the pressure transmitter 21, the fuel oil reaches the liquid inlet end of the second electromagnetic valve 16, the second electromagnetic valve 16 can output the fuel oil to the oil nozzle 22 and further eject the fuel oil from the oil nozzle, so that the high-energy igniter 18 can drive the ignition rod 23 to generate ignition spark to ignite the fuel oil, and the ignition experiment is realized. Meanwhile, redundant fuel oil in the combustion chamber 15 can return to the oil tank 2 through the electromagnetic valve III 17 and the valve II 14, so that the fuel oil can be fully combusted, excessive fuel oil loss in the combustion chamber 15 is avoided, and in the process of adjusting the fuel oil quantity, when the opening degree of the electromagnetic valve II 16 is small, the safety valve 6 and the electric pressure reducing valve 7 in the oil supply system can play a buffering role, the oil pressure in an ignition experiment system can be reduced, the experimental oil quantity is controlled more easily, the combustion efficiency of the fuel oil is improved, and the experiment precision is further improved.
Example 2
Referring to fig. 3 and fig. 4, the present embodiment provides an aviation fuel auto-ignition experimental apparatus, which further refines an ignition experimental system on the basis of embodiment 1. The ignition experiment system further comprises an oxygen inlet pipe, an oxygen flow controller 25, an oxygen supplementing valve 26, a smoke processor 27, a Roots blower 28, a low-pressure buffer tank 29, a water ring pump 30, an air flow controller 31 and an air supplementing valve 32. In addition, the combustion chamber 15 includes a reaction chamber 33, a vacuum gauge 34, and a plurality of windows 35.
The reaction chamber 33 is of a closed structure and has at least one inlet port through which oxygen enters. The fuel injection nozzle 22 and the ignition rod 23 are both provided in the reaction chamber 33, and the fuel is ignited in the reaction chamber 33. The inner wall of the reaction chamber 33 is a heat insulation layer, so that heat loss can be reduced, and the temperature generated by combustion in the combustion chamber 15 is more accurate. The vacuum gauge 34 is used to detect and display the degree of vacuum in the reaction chamber 33, so that the laboratory staff can grasp the vacuum state in the reaction chamber 33 in real time, and can find out in time especially when the air in the reaction chamber 33 is not exhausted to be clean. The window 35 is installed on the reaction chamber 33 and allows an external person to observe the combustion in the reaction chamber 33. The number of the windows 35 is four, and of the four windows 35, two windows 35 are quartz windows 35, and two windows 35 are infrared windows 35. After the vacuum is pumped, the vacuum condition in the reaction chamber 33 can be grasped in real time through the vacuum gauge 34, and the combustion condition in the reaction chamber 33 can be observed through the window 35, so that the ignition experiment can be conveniently carried out.
The oxygen inlet pipe is connected with the air inlet and is used for conveying oxygen to the air inlet. An oxygen replenishment valve 26 is mounted on the oxygen inlet tube and is used to open or close the oxygen inlet tube. An oxygen flow controller 25 is mounted on the oxygen inlet tube and is used to regulate the amount of oxygen entering the air inlet. The structures can provide oxygen for the reaction chamber 33, so that the experiment can be normally carried out, and meanwhile, an oxygen detection tube and an oxygen probe can be arranged, so that the oxygen content in the combustion chamber 15 can be detected in real time, the flow controller can control the oxygen supplementing valve 26 to supplement, the oxygen content in the combustion chamber 15 can be in any experiment concentration area, the experiment can be favorably carried out, and meanwhile, the situation of carrying out the experiment in the high-altitude low oxygen condition can be simulated.
The flue gas processor 27 is used for processing the flue gas generated in the combustion chamber 15 and conveying the flue gas to a low-pressure buffer tank 29 through a Roots blower 28. The low-pressure buffer tank 29 is used for buffering the flue gas treated by the flue gas processor 27 and outputting the flue gas through the water ring pump 30. The air flow controller 31 is used to regulate the flow of air from the make-up air valve 32 to the low pressure buffer tank 29. Thus, the flue gas generated from the reaction chamber 33 is processed by the flue gas processor 27 and then discharged through the roots blower 28, the low pressure buffer tank 29 and the water ring pump 30, so that the experiment can be continued.
Example 3
Referring to fig. 5, the present embodiment provides an aviation fuel auto-ignition experimental apparatus, which adds a partial structure on the basis of embodiment 2. The ignition experiment system further comprises a nitrogen inlet pipe, a nitrogen flow controller 37, a nitrogen supplementing valve 38, a gas phase sampling pipe, a valve III 40, an oxygen detection pipe, an oxygen probe 42, a valve IV 43, a dissolved oxygen detection pipe, a valve V45, a dissolved oxygen analyzer 46, a nitrogen detection pipe, a valve VI 48, a liquid phase sampling pipe, a valve VII 50, a drain pipe, a valve VIII 52, a vibration table 53, a solenoid valve IV 54, a valve VII 55, a filter I56, a cooling and heating device 57, a filter II 58, a valve V59, a solenoid valve V60, a water pump 61 and a temperature control pipe 62. Wherein, the working pressure range of the reaction chamber 33 is 0 to 5000 Pa.
The nitrogen inlet pipe is connected with the air inlet and is used for conveying nitrogen to the air inlet. The nitrogen supplement valve 38 is installed on the nitrogen inlet pipe and is used for opening or closing the nitrogen inlet pipe. A nitrogen flow controller 37 is installed on the nitrogen inlet pipe and serves to regulate the amount of nitrogen entering the gas inlet. In this embodiment, a hand valve may be further installed on the nitrogen inlet pipe, and the conduction and the closing of the nitrogen inlet pipe are controlled by the hand valve. Thus, when a fire is to be extinguished in the reaction chamber 33, a large amount of nitrogen gas can be introduced into the reaction chamber 33 through the nitrogen inlet pipe, and the oxygen inlet pipe is closed to stop oxygen supply and stop combustion, so that the combustion experiment can be ended. Of course, the oxygen inlet pipe and the nitrogen inlet pipe may be used as means for adjusting the gas composition in the reaction chamber 33 to change the ratio of oxygen to nitrogen.
The gas phase sampling tube is communicated with the combustion chamber 15, and the third valve 40 is used for opening or closing the gas phase sampling tube. Valve three 40 may be a hand valve that can facilitate the laboratory personnel in detecting the gas composition in reaction chamber 33. The oxygen probe tube is communicated with the combustion chamber 15, the oxygen probe 42 is used for detecting the oxygen concentration of the gas output from the oxygen probe tube, and the valve four 43 is used for opening or closing the oxygen probe tube. Similarly, the oxygen probe 42 can detect the oxygen content, so as to detect the oxygen concentration in the reaction chamber 33, so as to adjust the oxygen concentration through the oxygen inlet pipe.
The dissolved oxygen probe is in communication with the combustion chamber 15, the dissolved oxygen analyzer 46 is used to analyze the dissolved oxygen content of the gas flowing out of the dissolved oxygen probe, and the valve five 45 is used to open or close the dissolved oxygen probe. The nitrogen gas detection pipe is communicated with the combustion chamber 15, and a valve six 48 is used for opening or closing the nitrogen gas detection pipe. The nitrogen detection tube may provide a channel for detecting nitrogen so that an experimenter may extract gas from the tube to detect the content of nitrogen.
The liquid phase sampling tube is used for extracting liquid in the combustion chamber 15, and the valve seven 50 is used for opening or closing the liquid phase sampling tube. The liquid phase sampling tube can be used for the experimenter to carry out sampling test on the liquid generated by combustion so as to be convenient for detecting the experimental product. The blow-off pipe is in communication with the combustion chamber 15 and is used to discharge waste liquid resulting from combustion in the combustion chamber 15. Valve eight 52 is used to open or close the waste pipe. The vibration table 53 is used to vibrate the combustion chamber 15 to make the fuel uniformly distributed on the slit structure.
The temperature-controlled tube 62 is spirally or undulatedly bent in the reaction chamber 33, and is capable of absorbing or releasing heat into the reaction chamber 33. One end of the four solenoid valves 54 is communicated with one end of the temperature control pipe 62, and the other end of the four solenoid valves 54 is communicated with one end of the nine valve 55. One end of the first filter 56 communicates with the other end of the valve nine 55 and is used to filter the incoming liquid. The cooling and heating device 57 is a cooling and heating water tank or a cooling and heating unit, and is communicated with the other end of the first filter 56. One end of the second filter 58 is communicated with the cold and hot device 57, and the other end thereof is communicated with one end of the valve 59. One end of the five solenoid valve 60 is communicated with the other end of the valve ten 59, and the other end of the five solenoid valve 60 is communicated with the output end of the water pump 61. The output end of the water pump 61 is communicated with the other end of the temperature control pipe 62, so that a closed water circuit circulation system is formed by the water pump and the former components. The water circuit circulation system can convey cold water to the reaction chamber 33, and the cold water takes away heat, so that the temperature in the reaction chamber 33 is not too high due to the fact that the temperature in the reaction chamber 33 is reduced.
Example 4
The embodiment provides an aviation fuel automatic ignition experimental method which is applied to any one of the aviation fuel automatic ignition experimental devices provided in the embodiments 1 to 3. The aviation fuel oil automatic ignition experimental method comprises the following steps:
(1) storing fuel oil into the fuel tank 2, and starting the aviation fuel pump 4 to enable the fuel oil in the fuel tank 2 to pass through a first electromagnetic valve 5, a safety valve 6 and an electric pressure reducing valve 7 and return to the fuel tank 2;
(2) opening a first valve 13 to enable fuel output from the aviation fuel pump 4 to be delivered to a second electromagnetic valve 16;
(3) opening the second electromagnetic valve 16 to spray fuel from the fuel spray opening of the fuel spray nozzle 22;
(4) opening a third electromagnetic valve 17 to enable part of the fuel oil reaching the fuel spray nozzle 22 to flow back to the fuel tank 2;
(5) adjusting the opening degree of the first electromagnetic valve 5, the second electromagnetic valve 16 and the third electromagnetic valve 17 to enable the fuel quantity sprayed from the fuel injection port to reach a preset fuel quantity;
(6) the high-energy igniter 18 drives one end of the ignition rod 23 to generate an ignition spark so as to ignite fuel at the fuel injection port.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention.
Claims (10)
1. An aviation fuel automatic ignition experimental device is characterized by comprising an oil supply system, an ignition experimental system and a communicating assembly;
the oil supply system comprises a frame, an oil tank, a stop valve, an aviation fuel pump, a first electromagnetic valve, a safety valve and an electric pressure reducing valve; the fuel tank is arranged in the frame, is provided with at least one oil outlet end and at least one oil inlet end, and is used for storing fuel oil; the feed end of the stop valve is communicated with the oil outlet end of the oil tank, and the discharge end of the stop valve is communicated with the oil inlet end of the aviation fuel pump; the feed ends of the electromagnetic valve I, the safety valve and the electric pressure reducing valve are all communicated with the oil outlet end of the aviation fuel pump, and the discharge ends are all communicated with the oil inlet end of the oil tank;
the communication assembly comprises a first valve and a second valve; one end of the first valve is communicated with the oil outlet end of the aviation fuel pump; one end of the second valve is communicated with the first electromagnetic valve, the safety valve and the discharge end of the electric pressure reducing valve;
the ignition experiment system comprises a combustion chamber, a second electromagnetic valve, a third electromagnetic valve and a high-energy igniter; the combustion chamber comprises an oil nozzle and an ignition rod; the oil nozzle is communicated with the other end of the first valve through a second electromagnetic valve, and one end of the ignition rod is positioned in an oil nozzle of the oil nozzle; the high-energy igniter is connected with the other end of the ignition rod and enables the ignition rod to generate sparks in the fuel injection port so as to ignite fuel injected from the fuel injection port; and two ends of the electromagnetic valve III are respectively communicated with the other end of the valve II and the oil spray nozzle.
2. The aviation fuel auto-ignition experimental apparatus according to claim 1, wherein the combustion chamber further comprises a reaction chamber, a vacuum gauge and a plurality of windows; the reaction chamber is of a closed structure, and the oil nozzle and the ignition rod are both arranged in the reaction chamber; the vacuum gauge is used for detecting and displaying the vacuum degree in the reaction chamber; the window is installed on the reaction chamber and is used for external personnel to observe the combustion condition in the reaction chamber.
3. The aviation fuel oil automatic ignition experimental device is characterized in that the oil supply system further comprises an oil flow meter and a first pressure gauge; the fuel flow meter is used for displaying the flow of the fuel flowing out of the aviation fuel pump; and the pressure gauge is used for displaying the pressure of the fuel flowing out of the aviation fuel pump.
4. The aviation fuel oil automatic ignition experimental device is characterized in that the ignition experimental system further comprises a second pressure gauge, a temperature sensor and a pressure transmitter; the pressure gauge II is used for displaying the pressure of the fuel oil conveyed from the valve I to the electromagnetic valve II; the temperature sensor is used for detecting the temperature of the fuel conveyed from the first valve to the second solenoid valve; and the pressure transmitter is used for converting the pressure of the fuel oil conveyed to the electromagnetic valve II by the valve I into an electric signal.
5. The aviation fuel oil automatic ignition experimental device as claimed in claim 1, wherein the oil supply system further comprises a heating controller and an electromagnetic heater; the electromagnetic heater is arranged in the oil tank and is used for heating fuel oil in the oil tank; the electromagnetic heater is used for turning on or off the electromagnetic heater, and the temperature of the fuel in the fuel tank is kept within a preset fuel temperature range.
6. The aviation fuel oil automatic ignition experimental device as claimed in claim 2, wherein the reaction chamber is provided with at least one air inlet for oxygen to enter; the ignition experiment system also comprises an oxygen inlet pipe, an oxygen flow controller and an oxygen supplementing valve; the oxygen inlet pipe is connected with the air inlet and is used for conveying oxygen to the air inlet; the oxygen supplementing valve is arranged on the oxygen inlet pipe and is used for opening or closing the oxygen inlet pipe; the oxygen flow controller is installed on the oxygen inlet pipe and is used for adjusting the amount of oxygen entering the air inlet.
7. The aviation fuel oil automatic ignition experimental device as claimed in claim 1, wherein the ignition experimental system further comprises a flue gas processor, a roots blower, a low-pressure buffer tank, a water ring pump, an air flow controller and an air make-up valve; the flue gas processor is used for processing the flue gas generated in the combustion chamber and conveying the flue gas to the low-pressure buffer tank through the Roots blower; the low-pressure buffer tank is used for buffering the flue gas treated by the flue gas processor and outputting the flue gas through the water ring pump; the air flow controller is used for adjusting the flow of the air which is supplemented into the low-pressure buffer tank by the air supplementing valve.
8. The aviation fuel oil automatic ignition experimental device as claimed in claim 2, wherein the reaction chamber is provided with at least one air inlet for nitrogen to enter; the ignition experiment system also comprises a nitrogen inlet pipe, a nitrogen flow controller and a nitrogen supplementing valve; the nitrogen inlet pipe is connected with the gas inlet and is used for conveying nitrogen to the gas inlet; the nitrogen supplementing valve is arranged on the nitrogen inlet pipe and is used for opening or closing the nitrogen inlet pipe; the nitrogen flow controller is installed on the nitrogen inlet pipe and is used for adjusting the amount of nitrogen entering the air inlet.
9. The aviation fuel automatic ignition experimental device as claimed in claim 1, wherein the fuel spray nozzle is of a slit structure; the ignition experiment system also comprises a gas phase sampling tube, a valve III, an oxygen detecting tube, an oxygen probe, a valve IV, a dissolved oxygen detecting tube, a valve V, a dissolved oxygen analyzer, a nitrogen detecting tube, a valve VI, a liquid phase sampling tube, a valve VII, a blow-off tube, a valve VIII and a vibration table; the gas-phase sampling pipe is communicated with the combustion chamber, and the third valve is used for opening or closing the gas-phase sampling pipe; the oxygen detecting pipe is communicated with the combustion chamber, the oxygen probe is used for detecting the oxygen concentration of the gas output from the oxygen detecting pipe, and the valve IV is used for opening or closing the oxygen detecting pipe; the dissolved oxygen detecting tube is communicated with the combustion chamber, the dissolved oxygen analyzer is used for analyzing the dissolved oxygen content of gas flowing out of the dissolved oxygen detecting tube, and the valve five is used for opening or closing the dissolved oxygen detecting tube; the nitrogen detection pipe is communicated with the combustion chamber, and the sixth valve is used for opening or closing the nitrogen detection pipe; the liquid phase sampling pipe is used for extracting liquid in the combustion chamber, and the valve seventh is used for opening or closing the liquid phase sampling pipe; the blow-off pipe is communicated with the combustion chamber and is used for discharging waste liquid generated by combustion in the combustion chamber; the valve eight is used for opening or closing the sewage discharge pipe; the vibration table is used for vibrating the combustion chamber, so that fuel oil on the slit structure is uniformly distributed.
10. An aviation fuel automatic ignition experimental method applied to the aviation fuel automatic ignition experimental device as claimed in any one of claims 1 to 9, characterized by comprising the following steps:
(1) storing fuel oil into the fuel tank, and starting the aviation fuel pump to enable the fuel oil in the fuel tank to pass through the first electromagnetic valve, the safety valve and the electric pressure reducing valve and return to the fuel tank;
(2) opening the first valve to enable fuel output from the aviation fuel pump to be conveyed to the second electromagnetic valve;
(3) opening the second electromagnetic valve to enable the fuel to be sprayed out from the fuel spray opening of the fuel spray nozzle;
(4) opening the electromagnetic valve III to enable part of the fuel oil reaching the fuel spray nozzle to flow back to the fuel tank;
(5) adjusting the opening degree of the first electromagnetic valve, the second electromagnetic valve and the third electromagnetic valve to enable the fuel quantity sprayed from the fuel injection port to reach a preset fuel quantity;
(6) and driving one end of the ignition rod to generate an ignition flower through the high-energy igniter so as to ignite the fuel at the fuel injection port.
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