CN219533956U - Fire disaster simulator for multifunctional aircraft engine - Google Patents

Abstract

The utility model relates to the technical field of fire simulation equipment and discloses a fire simulation device of a multifunctional aircraft engine, which comprises a sealing box arranged in the aircraft engine, wherein the left end of the lower surface of the sealing box is connected with a cooling water outflow pipe, the right end of the lower surface of the sealing box is connected with a cooling water inflow pipe, a mixing mechanism is arranged in the sealing box, and a smoke generating mechanism is arranged at the left end of the lower surface of the interior of the sealing box; according to the utility model, through the arranged mixing structure, gaseous propane can be mixed into combustible gas and is ignited by the spark plug to generate flame, the flame burns vaporized liquid propane, so that a large amount of flame can be generated, the smoke generating machine directly sends smoke generating liquid in the smoke generating liquid box into a space between an aircraft engine and the sealing box after pressurization and atomization, and the atomized smoke generating liquid absorbs moisture in the air to form smoke, so that the simulation device can simulate smoke and fire at the same time, and the simulation effect is more fit with the actual situation.

Description

Fire disaster simulator for multifunctional aircraft engine

Technical Field

The utility model relates to the technical field of fire simulation equipment, in particular to a fire simulation device of a multifunctional aircraft engine.

Background

The fire disaster of the aircraft engine refers to the fire disaster caused by bird strike, foreign matter suction, faults and the like of the engine of the aircraft, and in order to train firefighters to rescue measures after the fire disaster occurs to the aircraft engine, the fire disaster simulation device of the aircraft engine is manufactured so that the firefighters can know the combustion process of the engine fire under the condition of safety and controllability; while a real engine accident usually has smoke, the traditional engine fire simulation device can only simulate fire simply and does not have the function of simulating smoke. Accordingly, one skilled in the art provides a multi-functional aircraft engine fire simulation device to address the problems set forth in the background above.

Disclosure of Invention

The utility model aims to provide a fire simulation device of a multifunctional aircraft engine, so as to solve the problems in the background technology.

In order to achieve the above purpose, the present utility model provides the following technical solutions:

the utility model provides a multi-functional aircraft engine fire analogue means, installs the seal box in aircraft engine inside including installing, the lower surface left end of seal box is connected with the cooling water outlet pipe, and the lower surface right-hand member of seal box is connected with the cooling water inflow pipe, the lower surface of seal box is located the left side of cooling water inflow pipe and runs through and install liquid propane input tube, a plurality of first through-hole has evenly been seted up to the upper surface right-hand member of liquid propane input tube, and a plurality of second through-hole has evenly been seted up to the right side surface of liquid propane input tube, the inside of seal box is provided with mixing mechanism, and the inside lower surface left end of seal box is provided with fuming mechanism.

As still further aspects of the utility model: the mixing mechanism comprises a mixing box, a gaseous propane input pipe is installed on the lower surface of the mixing box in a penetrating mode, an ignition tube is installed on the right side surface of the mixing box in a penetrating mode, a flame spray head is installed in the ignition tube, a spark plug high-pressure cap is installed on the left side of the mixing box, a spark plug guide pipe is connected with the right end of the spark plug high-pressure cap, a spark plug is connected with the right end of the spark plug guide pipe, an induced air fan is installed above the mixing box, a first air pipe is installed at the lower end of the induced air fan, and a second air pipe is installed at the left end of the induced air fan.

As still further aspects of the utility model: the smoke generating mechanism comprises a smoke generating machine and a smoke generating liquid box, a smoke discharging pipe is arranged on the lower surface of the smoke generating machine, and a connecting pipe is connected with the upper end of the smoke generating liquid box.

As still further aspects of the utility model: the cooling water outflow pipe and the cooling water inflow pipe penetrate through the lower surface of the aircraft engine, and the liquid propane input pipe penetrates through the right side surface of the sealing box.

As still further aspects of the utility model: the gas propane input pipe penetrates through the lower surfaces of the aircraft engine and the sealing box, the ignition pipe penetrates through the right side surface of the sealing box, the spark plug guide pipe is located inside the mixing box and the ignition pipe, the spark plug is located on the left side of the flame spray head, the first air pipe penetrates through the upper surface of the mixing box, and the second air pipe penetrates through the upper surfaces of the aircraft engine and the sealing box.

As still further aspects of the utility model: the smoke generator and the smoke generating liquid tank are both arranged on the lower surface of the interior of the sealing box, the smoke discharge pipe penetrates through the lower surface of the sealing box, and the upper end of the connecting pipe is connected to the smoke generator.

Compared with the prior art, the utility model has the beneficial effects that:

according to the utility model, the sealing box is double-layered, so that the damage to the internal equipment of the aircraft engine caused by high temperature can be avoided as much as possible, the mixing structure can mix air and gaseous propane into combustible gas and generate flame through ignition of the spark plug, the flame burns vaporized liquid propane, so that a large amount of flame can be generated, the smoke generator directly sends smoke liquid in the smoke liquid box into the space between the aircraft engine and the sealing box after pressurizing and atomizing, and the atomized smoke liquid absorbs moisture in the air to form smoke, so that the simulation device can simulate smoke and fire at the same time, and the simulation effect is more fit with the actual situation.

Drawings

FIG. 1 is a schematic diagram of a fire simulator of a multi-functional aircraft engine;

FIG. 2 is a schematic structural view of a hybrid mechanism in a multi-functional aircraft engine fire simulation device;

fig. 3 is a schematic structural view of a smoke generating mechanism in a fire simulator of a multifunctional aircraft engine.

In the figure: 1. an aircraft engine; 2. a seal box; 3. a cooling water outflow pipe; 4. a cooling water inflow pipe; 5. a liquid propane input pipe; 6. a first through hole; 7. a second through hole; 8. a mixing mechanism; 9. a smoke generating mechanism; 10. a mixing box; 11. a gaseous propane input pipe; 12. an ignition tube; 13. a flame spray head; 14. a spark plug high pressure cap; 15. a spark plug conduit; 16. a spark plug; 17. an induced air fan; 18. a first air duct; 19. a second air duct; 20. a smoke generator; 21. a smoke liquid box; 22. a smoke discharge pipe; 23. and (5) connecting pipes.

Detailed Description

Referring to fig. 1-3, in the embodiment of the utility model, the fire simulation device for the multifunctional aircraft engine comprises a seal box 2 installed inside the aircraft engine 1, a cooling water outflow pipe 3 is connected to the left end of the lower surface of the seal box 2, a cooling water inflow pipe 4 is connected to the right end of the lower surface of the seal box 2, the cooling water outflow pipe 3 and the cooling water inflow pipe 4 penetrate through the lower surface of the aircraft engine 1, a liquid propane input pipe 5 is installed on the lower surface of the seal box 2, the liquid propane input pipe 5 penetrates through the right surface of the seal box 2, a plurality of first through holes 6 are uniformly formed in the right end of the upper surface of the liquid propane input pipe 5, a plurality of second through holes 7 are uniformly formed in the right surface of the liquid propane input pipe 5, a mixing mechanism 8 is arranged inside the seal box 2, the mixing mechanism 8 comprises a mixing box 10, the lower surface of the mixing box 10 is provided with a gaseous propane input pipe 11 in a penetrating way, the gaseous propane input pipe 11 is provided with an ignition pipe 12 in a penetrating way through the lower surfaces of the aircraft engine 1 and the sealing box 2, the ignition pipe 12 is provided with a right side surface of the sealing box 2 in a penetrating way, a flame spray nozzle 13 is arranged in the ignition pipe 12, the left side of the mixing box 10 is provided with a spark plug high-pressure cap 14, the right end of the spark plug high-pressure cap 14 is connected with a spark plug guide pipe 15, the spark plug guide pipe 15 is positioned in the mixing box 10 and the ignition pipe 12, the right end of the spark plug guide pipe 15 is connected with a spark plug 16, the spark plug 16 is positioned at the left side of the flame spray nozzle 13, an induced draft fan 17 is arranged above the mixing box 10, the lower end of the induced draft fan 17 is provided with a first air pipe 18, the first air pipe 18 is provided with a second air pipe 19 in a penetrating way through the upper surface of the mixing box 10, the left end of the induced draft fan 17 is provided with a second air pipe 19, the second air duct 19 penetrates the upper surfaces of the aircraft engine 1 and the seal box 2; the sealed box is a box body with a double-layer hollow structure, and the middle of the double layers is used for circulating cooling water, so that the damage of high temperature to the internal equipment of the aircraft engine 1 is avoided; air is introduced into the interior of the mixing box 10 through the induced air blower 17, gaseous propane is fed into the interior of the mixing box 10 through the gaseous propane input pipe 11, the gaseous propane is also fed through the pressure equipment, the air and the gaseous propane are mixed into combustible gas, the combustible gas is ignited and burned through the ignition plug 16 and sprayed out through the flame spray 13, and the liquid propane is instantaneously vaporized when being output through the first through hole 6 and the second through hole 7 and is ignited by the flame.

In fig. 1 and 3: the left end of the inner lower surface of the seal box 2 is provided with a smoke generating mechanism 9, the smoke generating mechanism 9 comprises a smoke generating machine 20 and a smoke generating liquid box 21, the smoke generating machine 20 and the smoke generating liquid box 21 are both arranged on the inner lower surface of the seal box 2, a smoke discharging pipe 22 is arranged on the lower surface of the smoke generating machine 20, the smoke discharging pipe 22 penetrates through the lower surface of the seal box 2, the upper end of the smoke generating liquid box 21 is connected with a connecting pipe 23, smoke generating liquid is arranged in the smoke generating liquid box 21, and the upper end of the connecting pipe 23 is connected with the smoke generating machine 20; the smoke generator 20 pressurizes and atomizes the smoke generating fluid in the smoke generating fluid tank 21, and then directly sends the smoke generating fluid into the space between the aircraft engine 1 and the seal box 2, and the atomized smoke generating fluid absorbs moisture in the air to form smoke.

The working principle of the utility model is as follows: when the aircraft engine 1 is subjected to fire simulation, a worker can input cooling water into the inner wall of the seal box 2 through the cooling water inflow pipe 4, the cooling water flows out through the cooling water outflow pipe 3, high temperature damage to equipment in the aircraft engine 1 is avoided through the cooling water, then gaseous propane is input into the mixing box 10 through the gaseous propane input pipe 11, liquid propane is input into the liquid propane input pipe 5, an induced air fan 17 enters air from the outside to enable air and the gaseous propane to be mixed into combustible gas, then the spark plug 16 is ignited to enable the combustible gas to burn and be sprayed out through the flame spray nozzle 13, the liquid propane is instantaneously vaporized and is driven to burn by flame when being output through the first through hole 6 and the second through hole 7, meanwhile, the smoke generator 20 directly sends smoke in the smoke generating liquid box 21 into a space between the aircraft engine 1 and the seal box 2 after being pressurized and atomized, and the atomized smoke generating liquid absorbs moisture in the air to form smoke, so that the aircraft has all the characteristics of fire.

The foregoing description is only a preferred embodiment of the present utility model, but the scope of the present utility model is not limited thereto, and any person skilled in the art, who is within the scope of the present utility model, should make equivalent substitutions or modifications according to the technical solution of the present utility model and the inventive concept thereof, and should be covered by the scope of the present utility model.

Claims (6)

1. The utility model provides a multi-functional aircraft engine fire analog device, including installing at the inside seal box (2) of aircraft engine (1), its characterized in that, the lower surface left end of seal box (2) is connected with cooling water outlet pipe (3), and the lower surface right-hand member of seal box (2) is connected with cooling water inflow pipe (4), the lower surface of seal box (2) is located the left side of cooling water inflow pipe (4) and runs through and install liquid propane input tube (5), a plurality of first through-hole (6) have evenly been seted up to the upper surface right-hand member of liquid propane input tube (5), and a plurality of second through-hole (7) have evenly been seted up on the right side surface of liquid propane input tube (5), the inside of seal box (2) is provided with mixing mechanism (8), and the inside lower surface left end of seal box (2) is provided with fuming mechanism (9).

2. The multifunctional aircraft engine fire simulation device according to claim 1, wherein the mixing mechanism (8) comprises a mixing box (10), a gaseous propane input pipe (11) is installed in a penetrating manner on the lower surface of the mixing box (10), an ignition tube (12) is installed in a penetrating manner on the right side surface of the mixing box (10), a flame spray head (13) is installed in the ignition tube (12), a spark plug high-pressure cap (14) is installed on the left side of the mixing box (10), a spark plug guide pipe (15) is connected to the right end of the spark plug high-pressure cap (14), a spark plug (16) is connected to the right end of the spark plug guide pipe (15), an induced air fan (17) is installed above the mixing box (10), a first air pipe (18) is installed on the lower end of the induced air fan (17), and a second air pipe (19) is installed on the left end of the induced air fan (17).

3. A multi-functional aircraft engine fire simulation device according to claim 1, characterized in that the smoke generating mechanism (9) comprises a smoke generating machine (20) and a smoke generating liquid tank (21), a smoke discharging pipe (22) is arranged on the lower surface of the smoke generating machine (20), and a connecting pipe (23) is connected to the upper end of the smoke generating liquid tank (21).

4. A multi-functional aircraft engine fire simulation device according to claim 1, characterized in that the cooling water outflow pipe (3) and the cooling water inflow pipe (4) each penetrate the lower surface of the aircraft engine (1), and the liquid propane input pipe (5) penetrates the right side surface of the seal box (2).

5. The fire simulator of the multifunctional aircraft engine according to claim 2, wherein the gaseous propane input pipe (11) penetrates through the lower surfaces of the aircraft engine (1) and the sealing box (2), the ignition pipe (12) penetrates through the right side surface of the sealing box (2), the spark plug conduit (15) is located inside the mixing box (10) and the ignition pipe (12), the spark plug (16) is located on the left side of the flame spray head (13), the first air pipe (18) penetrates through the upper surface of the mixing box (10), and the second air pipe (19) penetrates through the upper surfaces of the aircraft engine (1) and the sealing box (2).

6. A fire simulator for a multi-functional aircraft engine according to claim 3, wherein the smoke generator (20) and the smoke liquid tank (21) are mounted on the inner lower surface of the sealing box (2), the smoke discharge pipe (22) penetrates the lower surface of the sealing box (2), and the upper end of the connecting pipe (23) is connected to the smoke generator (20).