Aircraft fire extinguishing agent effectiveness test apparatus

Abstract

The application provides an aviation fire extinguishing agent effect test device, and belongs to the field of fire extinguishing agents. The aviation fire extinguishing agent effect test device comprises a bearing frame for supporting a simulation cabin, a fire extinguishing agent tank and a combustion agent tank, the side surface of the simulation cabin is provided with a heating assembly and a cooling assembly for adjusting temperature, the inside of the bearing frame is provided with a conduction mechanism for conducting combustion agent to the inside of the simulation cabin and igniting, and the top of the simulation cabin is fixedly provided with a cover plate for closing the simulation cabin and guaranteeing the pressure in the simulation cabin. Through independent design of the high-temperature simulation cabin and the low-temperature simulation cabin, cooperation of the heating assembly, the cooling assembly and the surrounding heating pipe and the cooling pipe, the high-temperature cabin of the aviation engine and the high-altitude low-temperature environment can be accurately simulated; the grouping of the turbo vacuum pump and the booster pump can adjust the air pressure of different cabin bodies, fully restore the extreme conditions of high altitude, and solve the problem of insufficient environment restoration degree of the traditional device, thereby improving the reliability of the test data.

Description

Technical Field

[0001] This application relates to the field of fire extinguishing agents, and more specifically, to a testing device for the effectiveness of aviation fire extinguishing agents. Background Technology

[0002] The aviation fire extinguishing agent effectiveness testing device is a specialized testing equipment designed to evaluate the fire extinguishing effectiveness, applicability, and safety of aviation fire extinguishing agents. It simulates potential fire types in aviation scenarios, precisely controlling conditions such as fire source intensity, ambient temperature, and fire extinguishing agent injection parameters. It monitors key indicators in real time, including extinguishing time, flame suppression effect, and residue impact, providing scientific data support for the research, development, performance certification, and safe application of aviation fire extinguishing agents.

[0003] Chinese patent application number 201920289164.9 discloses a testing device for fire extinguishing agent production, comprising a combustion chamber, a support frame, a height adjustment motor, a height adjustment motor support base, an adjustment screw, a moving nut, a connecting frame, a fire extinguisher retaining ring, a height scale, a fire extinguisher, a fire extinguisher valve, a fire extinguisher nozzle, a fire extinguishing agent valve ignition rod, a rotating hinge, an ignition gun, a burning material support frame, a burning material support net, a combustible gas inlet pipe, a combustible gas combustion nozzle, a combustible gas inlet pipe valve, and a connecting sleeve. The support frame is located at the top of the combustion chamber and is fixedly connected to it. This invention solves the problem that current methods for testing the fire extinguishing performance of water-based fire extinguishing agents rely on manual methods for testing various materials. These methods are not only inaccurate but also dangerous, failing to meet the testing requirements for water-based fire extinguishing agents. Furthermore, this invention is convenient and safe to operate, can meet the fire extinguishing performance testing requirements of different types of combustibles targeted by water-based fire extinguishing agents, and offers high testing accuracy, satisfying the production and usage needs of enterprises.

[0004] The above-mentioned scheme has the following shortcomings: The fire extinguishing agent testing device has a narrow scope of application and can only test conventional fire extinguishing agents. It has obvious limitations in terms of environmental and scene reproduction and cannot simulate the high temperature environment of aircraft engine compartments and the extreme conditions of high altitude, low temperature and low pressure, which makes it difficult to fully reflect the special characteristics of high-altitude fires. Utility Model Content

[0005] To overcome the above shortcomings, this application provides an aviation fire extinguishing agent effect testing device, which aims to improve the problem that the test effect of aviation fire extinguishing agents in the special circumstances of high-altitude fires is difficult to fully reflect, thus reducing the practicality of the device.

[0006] This application provides an aviation fire extinguishing agent effect testing device, including a support frame for supporting a simulation chamber, a fire extinguishing agent tank, and a combustion agent tank. The side of the simulation chamber is equipped with a heating component and a cooling component for temperature regulation. The inside of the support frame is equipped with a conduction mechanism for conducting combustion agent into the simulation chamber and igniting it. The top of the simulation chamber is fixedly equipped with a cover plate for sealing the simulation chamber and ensuring the pressure inside the simulation chamber. A turbo vacuum pump and a booster pump for regulating the air pressure inside the simulation chamber are installed on the top of the cover plate.

[0007] In one specific implementation, the simulation chamber includes a high-temperature simulation chamber and a low-temperature simulation chamber, wherein the interior of the high-temperature simulation chamber and the low-temperature simulation chamber are provided with a mezzanine, wherein heating pipes and cooling pipes that are connected to heating components and cooling components are respectively installed in the mezzanine.

[0008] In the above implementation process, high-temperature simulation chambers and low-temperature simulation chambers are used to simulate different temperature scenarios under the condition of aircraft flying at high altitude.

[0009] In one specific implementation, the heating component uses an inert gas thermal circulation device to simulate the extreme high-temperature environment of an aircraft engine combustion chamber fire, and the cooling component uses liquid nitrogen-assisted cooling to simulate the low-temperature scenario during high-altitude cruise.

[0010] In the above implementation process, heating components are used to simulate the high-temperature environment inside the aircraft engine compartment, while cooling components are used to simulate the low-temperature scenario during high-altitude cruise of the aircraft.

[0011] In one specific implementation, the top of the extinguishing agent tank is equipped with a transfer pump for transmitting the extinguishing agent and a transfer pipe for transmitting the extinguishing agent, wherein the other end of the transfer pipe is installed on the top of a cover plate, and an extinguishing agent nozzle is provided at the bottom of the cover plate.

[0012] In the above process, the extinguishing agent is sprayed out through the extinguishing agent nozzle at the bottom of the cover plate by the conduction pump to achieve the effect of extinguishing the fire.

[0013] In one specific implementation, temperature sensors for feedback of the cabin temperature are distributed inside the simulation chamber.

[0014] In the above implementation process, temperature sensors provide real-time feedback on the temperature changes in the simulation chamber, facilitating the collection of fire extinguishing data.

[0015] In one specific implementation, the transmission mechanism includes a transfer pump for transmitting the propellant. The input end and output end of the transfer pump are respectively equipped with a suction pipe connected to the propellant tank and a diversion pipe connected to the simulation chamber. An igniter is provided at the top of the diversion pipe and at the inner bottom of the simulation chamber. The igniters are distributed at the inner bottom of the simulation chamber.

[0016] In the above process, a transfer pump, in conjunction with a suction pipe and a diversion pipe, is used to transfer the propellant in the propellant tank to the simulation chamber and ignite it to simulate a fire situation.

[0017] In one specific implementation, the heating and cooling pipes are designed to be wrapped around each other, and the heating and cooling pipes are wrapped around the interlayer of the high-temperature simulation chamber and the low-temperature simulation chamber.

[0018] In the above implementation process, the temperature coverage range is increased by using a surround design, thereby improving the efficiency of temperature regulation.

[0019] In one specific implementation, the outer wall of the simulation chamber is made of heat-insulating material, and the interior is made of heat-conducting material.

[0020] In the above process, it plays a role in reducing heat leakage and improving heat conduction efficiency.

[0021] In one specific implementation, the turbo vacuum pump and the booster pump are provided in two sets, which are respectively connected to the high-temperature simulation chamber and the low-temperature simulation chamber.

[0022] In the above implementation process, it is convenient to adjust the air pressure values ​​of the high temperature simulation chamber and the low temperature simulation chamber to simulate high-altitude flight conditions, so as to improve the accuracy of the test.

[0023] In one specific implementation, the surfaces of the extinguishing agent tank and the combustion agent tank are provided with filling ports.

[0024] The above implementation process facilitates the timely addition of extinguishing agents and combustion agents to the interior of the extinguishing agent tank and the combustion agent tank.

[0025] Compared with existing technologies, the beneficial effects of this application are as follows: through the independent design of high-temperature simulation chamber and low-temperature simulation chamber, combined with heating components, cooling components and surrounding heating pipes and cooling pipes, the high temperature and high-altitude low temperature environment of aircraft engine compartment can be accurately simulated; the group setting of turbovacuum pump and booster pump can adjust the air pressure of different chambers, fully restore the extreme conditions at high altitude, solve the problem of insufficient environmental reproduction of traditional devices, and improve the reliability of test data. Attached Figure Description

[0026] To more clearly illustrate the technical solutions of the embodiments of this application, the drawings used in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of this application and should not be regarded as a limitation of the scope. For those skilled in the art, other related drawings can be obtained from these drawings without creative effort.

[0027] Figure 1 This is a three-dimensional structural diagram provided in the embodiments of this application;

[0028] Figure 2 A rear view structural diagram provided for an embodiment of this application;

[0029] Figure 3 A front view structural diagram provided for an embodiment of this application;

[0030] Figure 4 A side view structural diagram provided for an embodiment of this application;

[0031] Figure 5 A schematic diagram of the cover plate disassembly structure provided for an embodiment of this application;

[0032] Figure 6 A schematic diagram of the internal structure of the simulation cabin provided for the embodiments of this application;

[0033] Figure 7 A schematic diagram of the structure inside the simulated cabin interlayer provided for the embodiments of this application;

[0034] Figure 8 This is a side view of the transmission mechanism provided in an embodiment of this application.

[0035] In the diagram: 1. Support frame; 2. Extinguishing agent tank; 21. Conductive pump; 22. Transfer pipe; 23. Extinguishing agent nozzle; 3. Simulation chamber; 31. High-temperature simulation chamber; 32. Low-temperature simulation chamber; 4. Cover plate; 41. Turbine vacuum pump; 42. Booster pump; 5. Heating assembly; 51. Heating pipe; 6. Cooling assembly; 61. Cooling pipe; 62. Temperature sensor; 7. Propellant tank; 8. Conductive mechanism; 81. Transfer pump; 82. Suction pipe; 83. Diverter pipe; 84. Ignition device. Detailed Implementation

[0036] The technical solutions in the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments.

[0037] Please see Figure 1-8 This application provides an aviation fire extinguishing agent effect testing device, including a support frame 1 for supporting a simulation chamber 3, a fire extinguishing agent tank 2, and a combustion agent tank 7. The surfaces of the fire extinguishing agent tank 2 and the combustion agent tank 7 are provided with filling ports with sealed caps, facilitating the timely addition of fire extinguishing agent and combustion agent to the interior of the fire extinguishing agent tank 2 and the combustion agent tank 7.

[0038] The top of the extinguishing agent tank 2 is equipped with a conduction pump 21 for transmitting the extinguishing agent and a transmission pipe 22 for transmitting the extinguishing agent. The conduction pump 21 is a corrosion-resistant centrifugal pump, and its flow rate can be adjusted by a frequency converter to adapt to the viscosity characteristics of different extinguishing agents. The other end of the transmission pipe 22 is installed on the top of the cover plate 4. The bottom of the cover plate 4 is equipped with an extinguishing agent nozzle 23. The extinguishing agent nozzle 23 is a multi-hole atomizing nozzle. After the extinguishing agent is pressurized by the conduction pump 21, it is delivered to the extinguishing agent nozzle 23 at the bottom of the cover plate 4 through the transmission pipe 22 to form a fine mist spray, ensuring that the extinguishing agent is evenly covered in the simulation chamber 3 to achieve the effect of efficient fire extinguishing.

[0039] The outer wall of the simulation chamber 3 is made of aluminum silicate cotton insulation material, and the outer wall surface is covered with stainless steel protective plate. The interior is made of 316 stainless steel thermal conductive material, which not only reduces heat leakage and energy consumption, but also improves the temperature conduction efficiency inside the chamber and ensures the temperature uniformity inside the chamber. Temperature sensors 62 are distributed inside the simulation chamber 3 to provide feedback on the temperature inside the chamber. The temperature sensors 62 are K-type thermocouples with a measurement range of -200℃ to 1200℃. The temperature sensors 62 provide real-time feedback on the temperature changes inside the simulation chamber 3, which facilitates the comprehensive collection and analysis of temperature data during the fire extinguishing process.

[0040] The simulation chamber 3 includes a high-temperature simulation chamber 31 and a low-temperature simulation chamber 32. Both chambers are symmetrical in structure and operate independently. Each chamber has an annular interlayer, within which heating pipes 51 and cooling pipes 61, connected to heating assembly 5 and cooling assembly 6, are installed. Both heating pipes 51 and 61 are made of copper and feature a continuous, encircling design. They are tightly fitted to the inner walls of the interlayer in both chambers. This encircling design increases the contact area with the chamber structure, improving the efficiency and uniformity of temperature regulation. The high-temperature and low-temperature simulation chambers 31 and 32 can simulate extreme high and low temperature scenarios during high-altitude flight, meeting the needs of fire extinguishing tests under different environments.

[0041] The side of the simulation cabin 3 is equipped with a heating component 5 and a cooling component 6 for temperature regulation. The heating component 5 adopts an inert gas thermal circulation device, including an electric heating furnace, a circulating fan and a gas purification module. Thermal circulation inert gas is introduced into the interlayer of the high-temperature simulation cabin 31 through the heating pipe 51 to heat the cabin temperature and simulate the high-temperature environment of an aircraft engine combustion chamber fire. The cooling component 6 adopts a liquid nitrogen-assisted cooling system, including a liquid nitrogen storage tank, a vaporizer and a flow control valve. Cooling energy is introduced into the interlayer of the low-temperature simulation cabin 32 through the cooling pipe 61 to simulate the low-temperature scenario of the aircraft cruising at high altitude. Through the precise control of the heating component 5 and the cooling component 6, the environmental temperature of different cabin sections of the aircraft can be realistically simulated.

[0042] The carrier frame 1 is equipped with a transmission mechanism 8 for transferring the propellant to the interior of the simulation chamber 3 and igniting it. The transmission mechanism 8 includes a transfer pump 81 for transferring the propellant. The transfer pump 81 is an explosion-proof gear pump, which is compatible with various types of propellants such as aviation kerosene and hydraulic oil. The input and output ends of the transfer pump 81 are respectively equipped with a suction pipe 82 connected to the propellant tank 7 and a diversion pipe 83 connected to the simulation chamber 3. An igniter 84 is installed at the top of the diversion pipe 83 and at the bottom of the simulation chamber 3. The igniter 84 is an electric spark ignition device. Multiple igniters 84 are evenly distributed in each simulation chamber. The propellant flow rate is precisely controlled by the transfer pump 81. With the help of the suction pipe 82 and the diversion pipe 83, the propellant in the propellant tank 7 is evenly transferred to each ignition point in the simulation chamber 3. Then, it is ignited by the igniter 84 to form a stable flame, accurately simulating aviation fires of different scales.

[0043] The top of the simulation chamber 3 is fixedly equipped with a cover plate 4 for sealing the simulation chamber 3 and ensuring the pressure inside the simulation chamber 3. The cover plate 4 is bolted to achieve a tight seal. The top of the cover plate 4 is equipped with a turbine vacuum pump 41 and a booster pump 42 for adjusting the air pressure inside the simulation chamber 3. The turbine vacuum pump 41 can reduce the air pressure inside the chamber to 0.05MPa to simulate the air pressure at an altitude of 10,000 meters. The booster pump 42 can increase the air pressure inside the chamber to 0.2MPa to simulate the air pressure at ground or low altitude. There are two sets of each turbine vacuum pump 41 and booster pump 42, which are independently connected to the high temperature simulation chamber 31 and the low temperature simulation chamber 32 through valves. This allows for the adjustment of different air pressure values ​​inside the high temperature simulation chamber 31 and the low temperature simulation chamber 32 according to the test requirements, accurately simulating the air pressure environment of an aircraft at different flight altitudes, thereby improving the accuracy and reliability of the fire extinguishing effect test of the fire extinguishing agent.

[0044] The working principle of this aviation fire extinguishing agent effect testing equipment is as follows: During the test, in the simulation chamber 3 supported by the support frame 1, the high-temperature simulation chamber 31 is heated by the heating component 5 through the heating pipe 51 and the inert gas is introduced to raise the temperature. The low-temperature simulation chamber 32 is cooled by the cooling component 6 through the cooling pipe 61 and the temperature sensor 62 provides real-time feedback on the temperature inside the chamber. After the turbine vacuum pump 41 and the booster pump 42 adjust the air pressure of the two chambers to the target value, the transmission pump 81 of the transmission mechanism 8 draws the combustion agent from the combustion agent tank 7 through the suction pipe 82 and delivers it to the bottom of the simulation chamber 3 through the diversion pipe 83, where it is ignited by the igniter 84 to form a simulated fire. During the fire extinguishing stage, the fire extinguishing agent in the fire extinguishing agent tank 2 is pressurized by the transmission pump 21 and delivered to the fire extinguishing agent nozzle 23 at the bottom of the cover plate 4 through the transmission pipe 22 and atomized. The equipment records data such as temperature, air pressure and fire extinguishing time simultaneously to complete the fire extinguishing agent effect test under different environments.

[0045] The above are merely specific embodiments of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. An aviation fire extinguishing agent effect testing device, comprising a support frame (1) for supporting a simulation chamber (3), a fire extinguishing agent tank (2), and a combustion agent tank (7), characterized in that, The simulation chamber (3) is equipped with a heating component (5) and a cooling component (6) for adjusting the temperature. The inside of the support frame (1) is equipped with a conduction mechanism (8) for conducting the propellant to the inside of the simulation chamber (3) and igniting it. The top of the simulation chamber (3) is fixedly equipped with a cover plate (4) for sealing the simulation chamber (3) and ensuring the pressure inside the simulation chamber (3). The top of the cover plate (4) is equipped with a turbo vacuum pump (41) and a booster pump (42) for adjusting the air pressure inside the simulation chamber (3).

2. The aviation fire extinguishing agent effect testing equipment according to claim 1, characterized in that, The simulation chamber (3) includes a high temperature simulation chamber (31) and a low temperature simulation chamber (32). The interior of the high temperature simulation chamber (31) and the low temperature simulation chamber (32) is provided with a sandwich layer, in which heating pipe (51) and cooling pipe (61) connected to heating component (5) and cooling component (6) are respectively installed.

3. The aviation fire extinguishing agent effect testing equipment according to claim 2, characterized in that, The heating component (5) uses an inert gas thermal circulation device to simulate the extreme high temperature environment of an aircraft engine combustion chamber fire, and the cooling component (6) uses liquid nitrogen-assisted cooling to simulate the low temperature scenario during high-altitude cruise.

4. The aviation fire extinguishing agent effect testing equipment according to claim 3, characterized in that, The top of the extinguishing agent tank (2) is equipped with a transfer pump (21) for transferring extinguishing agent and a transfer pipe (22) for transferring extinguishing agent. The other end of the transfer pipe (22) is installed on the top of the cover plate (4), and the bottom of the cover plate (4) is provided with an extinguishing agent nozzle (23).

5. The aviation fire extinguishing agent effect testing equipment according to claim 4, characterized in that, The interior of the simulation chamber (3) is equipped with temperature sensors (62) for feeding back the temperature inside the chamber.

6. The aviation fire extinguishing agent effect testing equipment according to claim 5, characterized in that, The transmission mechanism (8) includes a transfer pump (81) for transmitting the propellant. The input end and output end of the transfer pump (81) are respectively equipped with a suction pipe (82) connected to the propellant tank (7) and a diversion pipe (83) connected to the simulation chamber (3). An igniter (84) is provided at the top of the diversion pipe (83) and at the bottom of the simulation chamber (3). The igniter (84) is distributed at the bottom of the simulation chamber (3).

7. The aviation fire extinguishing agent effect testing equipment according to claim 6, characterized in that, The heating pipe (51) and cooling pipe (61) are designed to surround each other, and the heating pipe (51) and cooling pipe (61) are wrapped in the interlayer of the high temperature simulation chamber (31) and the low temperature simulation chamber (32).

8. The aviation fire extinguishing agent effect testing equipment according to claim 7, characterized in that, The outer wall of the simulation chamber (3) is made of heat-insulating material, and the interior is made of heat-conducting material.

9. The aviation fire extinguishing agent effect testing equipment according to claim 8, characterized in that, Two sets of turbo vacuum pump (41) and booster pump (42) are provided, and are respectively connected to the high temperature simulation chamber (31) and the low temperature simulation chamber (32).

10. The aviation fire extinguishing agent effect testing equipment according to claim 9, characterized in that, The surfaces of the extinguishing agent tank (2) and the combustion agent tank (7) are provided with filling ports.

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