Aviation fuel oil automatic ignition experimental device and experimental method thereof
An aviation fuel and auto-ignition technology, which is applied in the fields of aviation fuel auto-ignition experiments, experimental devices, and aviation fuel auto-ignition experimental devices, can solve the problems of insufficient combustion and uncontrollable fuel volume, and achieves the goal of improving accuracy and ensuring normal circulation. Effect
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Embodiment 1
[0067] see figure 1 as well as figure 2 , the present embodiment provides an aviation fuel auto-ignition experimental device, which is used for auto-ignition experiments on aviation fuel, and can simulate the ignition effect of fuel in different aviation environments. Among them, the aviation fuel automatic ignition experimental device includes a fuel supply system, an ignition experimental system and a Unicom component. Since the fuel supply system is connected to the ignition test system through the Unicom component, the separation of the fuel supply system and the ignition test system can be realized, and the distance between the two can be very far, thus reducing the risk of deflagration caused by the ignition test system to the fuel supply system Possibility, especially in the high temperature situation during the ignition experiment, the oil supply system can be isolated from the high temperature experiment environment to make the ignition experiment safer, and the ign...
Embodiment 2
[0079] see image 3 as well as Figure 4 , this embodiment provides an aviation fuel automatic ignition experimental device, which further refines the ignition experimental system on the basis of Embodiment 1. Among them, the ignition experiment system also includes an oxygen inlet pipe, an oxygen flow controller 25, an oxygen supply valve 26, a flue gas processor 27, a Roots blower 28, a low-pressure buffer tank 29, a water ring pump 30, an air flow controller 31 and a supplementary valve. Air valve 32. In addition, the combustion chamber 15 also includes a reaction chamber 33 , a vacuum gauge 34 and a plurality of windows 35 .
[0080] The reaction chamber 33 is a closed structure and has at least one gas inlet for oxygen to enter. Both the fuel injector 22 and the ignition rod 23 are arranged 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 insulating layer, which can reduce heat loss a...
Embodiment 3
[0084] see Figure 5 , this embodiment provides an aviation fuel auto-ignition experimental device, which adds part of the structure on the basis of Embodiment 2. Among them, the ignition experiment system also includes nitrogen inlet pipe, nitrogen flow controller 37, nitrogen supplement valve 38, gas phase sampling pipe, valve three 40, oxygen detection pipe, oxygen probe 42, valve four 43, dissolved oxygen detection pipe, valve five 45 , dissolved oxygen analyzer 46, nitrogen detection tube, valve six 48, liquid phase sampling tube, valve seven 50, sewage pipe, valve eight 52, vibration table 53, solenoid valve four 54, valve nine 55, filter one 56, cooling Thermal device 57, filter two 58, valve ten 59, electromagnetic valve five 60, water pump 61 and temperature control pipe 62. Wherein, the working pressure range of the reaction chamber 33 is 0-5000Pa.
[0085] The nitrogen inlet pipe is connected with the air inlet, and is used to deliver nitrogen to the air inlet. N...
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