CN215136210U

CN215136210U - Automatic cover and gas of packing up and use isolated device of putting out a fire

Info

Publication number: CN215136210U
Application number: CN202120355667.9U
Authority: CN
Inventors: 吴定洪; 刘亮; 陈定海; 李斐然; 王庆; 彭梁; 汪倩芸; 戢行毅; 胡斌; 王妍萍; 江华健; 李伟
Original assignee: Vitalong Fire Safety Group Co Ltd
Current assignee: Vitalong Fire Safety Group Co Ltd
Priority date: 2021-02-06
Filing date: 2021-02-06
Publication date: 2021-12-14
Anticipated expiration: 2031-02-06

Abstract

The utility model belongs to the technical field of extinguishing device, concretely relates to automatic cover and gas of packing up are put out a fire and are used isolated device. The technical scheme is as follows: an isolating device for gas fire extinguishing, which can automatically cover and retract, comprises isolating cloth for surrounding an aircraft engine, wherein the isolating cloth is cylindrical and is connected to an aircraft engine hanger, and a gas nozzle is arranged on the aircraft engine hanger; the winding mechanism is characterized in that a winding driving mechanism is installed on the aircraft engine hanger, the output end of the winding driving mechanism is connected with a driving winding wheel, a plurality of driven winding wheels are installed on the aircraft engine hanger, a transmission mechanism is connected between the driving winding wheel and the driven winding wheels, pull wires are wound on the driving winding wheel and the driven winding wheels, and the other ends of the pull wires are connected with the lower end of the isolation cloth. The utility model provides an automatic cover and the gaseous isolated device of using of putting out a fire that packs up.

Description

Automatic cover and gas of packing up and use isolated device of putting out a fire

Technical Field

The utility model belongs to the technical field of extinguishing device, concretely relates to automatic cover and gas of packing up are put out a fire and are used isolated device.

Background

For equipment which runs in open air or open scenes such as large open-air power transmission and transformation transformers, large oil and gas field exploitation fracturing units, aeroengines and high-altitude simulation test beds, if fire disasters caused by out-of-control combustion occur, serious economic loss and social influences are caused. Because the best effect can be achieved only by adopting a gas fire extinguishing mode in a limited space, the fire behavior is difficult to control by adopting gas fire extinguishing under the working conditions of the open air and open scenes.

An aerial engine high-altitude simulation test bed is called a high-altitude bed for short, and is system equipment for simulating the flying condition and environment of an aircraft engine in the air on the ground and carrying out high-altitude simulation tests on the whole engine and parts. The scientific test of various functions, performances and technical and tactical indexes when the aero-engine is simulated to fly on the high-altitude platform is an important and necessary stage in the development process of the design, the shaping and the improvement and the modification of the aero-engine, and is an indispensable means for developing the advanced aero-engine and the improvement and the modification thereof. In order to research and develop an advanced aero-engine, a large number of tests must be carried out on an aero-engine high-altitude simulation test bed so as to analyze, study, verify and examine the performance, functions, acceleration and deceleration characteristics, working stability, air starting special force connection characteristics, working performances of systems such as lubricating oil and the like of the aero-engine and parts thereof. Through high altitude simulation test, can effectively verify technical scheme, provide technical support for developing high-efficient driving system. The high-altitude simulation test is the most effective way for designing, improving and modifying the aero-engine, technical attack and failure reproduction and elimination.

In the process of testing the aircraft engine at the high-altitude platform, when the aircraft engine is on fire, the conventional gas fire extinguishing mode is difficult to extinguish the fire quickly and reliably. The high-altitude platform is located spacious indoor, and when using gases such as carbon dioxide to put out a fire, gas is difficult to reach higher concentration around aircraft engine to the ignition point on the aircraft engine is difficult to put out a fire fast. When gas is used for extinguishing fire, the fire extinguishing efficiency can be improved only by reducing the emission of the gas.

SUMMERY OF THE UTILITY MODEL

In order to solve the problems existing in the prior art, the utility model aims to provide an automatic cover and the gas who packs up are put out a fire with isolated device.

The utility model discloses the technical scheme who adopts does:

an isolating device for gas fire extinguishing, which can automatically cover and retract, comprises isolating cloth for surrounding an aircraft engine, wherein the isolating cloth is cylindrical and is connected to an aircraft engine hanger, and a gas nozzle is arranged on the aircraft engine hanger; the winding mechanism is characterized in that a winding driving mechanism is installed on the aircraft engine hanger, the output end of the winding driving mechanism is connected with a driving winding wheel, a plurality of driven winding wheels are installed on the aircraft engine hanger, a transmission mechanism is connected between the driving winding wheel and the driven winding wheels, pull wires are wound on the driving winding wheel and the driven winding wheels, and the other ends of the pull wires are connected with the lower end of the isolation cloth.

When the aircraft engine fires in a test, the winding driving mechanism is started, and drives the driving winding wheel to rotate. When the driving winding wheel rotates, the driving winding wheel drives the driven winding wheel to rotate through the transmission mechanism. The active winding wheel and the driven winding wheel wind the stay wire out, so that the isolation cloth can hang down under the action of gravity and surround the aircraft engine. The gas nozzle sprays gas to the area between the isolation cloth and the aircraft engine, so that the concentration of fire extinguishing gas around the aircraft engine is quickly improved, and the aircraft engine is quickly extinguished. The isolation cloth can prevent the fire extinguishing gas from diffusing and ensure that the fire extinguishing gas forms a full-submerged environment around the aircraft engine.

As the utility model discloses an optimal scheme, rolling actuating mechanism includes the motor, and the output shaft of motor has the reduction gear, and motor and reduction gear are all installed on aircraft engine gallows, and the initiative wind-up pulley is connected on the output shaft of reduction gear. After the motor is started, the motor drives the speed reducer to act, the speed reducer drives the driving winding wheel to rotate, the driving winding wheel can fold or put down the stay wire on the side, and the driving winding wheel can drive the driven winding wheel to rotate through the transmission mechanism.

As the utility model discloses an optimal scheme, drive mechanism includes drive sprocket, and drive sprocket connects on the initiative rolling wheel, is connected with driven sprocket on the aircraft engine gallows, and drive sprocket and driven sprocket pass through chain drive and connect, are connected with the driving gear on the driven sprocket, and driven rolling takes turns to and is connected with driven gear, driving gear and driven gear meshing. When the driving winding wheel rotates, the driving chain wheel correspondingly rotates, and the driving chain wheel drives the driven chain wheel to rotate through the chain. When the driven chain wheel rotates, the driving gear correspondingly rotates and drives the driven gear to rotate. When the driven gear rotates, the driven winding wheel correspondingly rotates and the side pull wire is wound up or put down. After transmission of the transmission mechanism, the driving winding wheel and the driven winding wheel are opposite in rotation direction, and all sides of the isolation cloth are guaranteed to be simultaneously folded or simultaneously put down, so that control is facilitated.

As the preferred scheme of the utility model, the lower extreme of isolated cloth is fixed with the weight piece, and the stay cord is connected in the position that the weight piece was connected to isolated cloth. The weight block enables the isolated cloth to be pulled down, so that the isolated cloth can smoothly surround the aircraft engine, and the utility model discloses it is more reliable. The weight block can also tighten the stay wire, so that the stay wire can be accurately wound on the driving winding wheel or the driven winding wheel, and the looseness of the stay wire is avoided.

As the utility model discloses an optimal scheme, the other pinch roller that is used for acting as go-between to compress tightly that all is provided with of initiative rolling wheel and driven rolling wheel. The pinch roller can compress tightly acting as go-between, avoids acting as go-between not hard up on initiative rolling wheel or driven rolling wheel, guarantees to act as go-between the reliability of pulling the isolated cloth.

As the utility model discloses an optimal scheme, be provided with the spout on the aircraft engine gallows, the spout endotheca is equipped with the slider, and the pinch roller rotates to be connected on the slider, is connected with the spring between the bottom of spout and the slider. The spring can be with slider up-pushing, then the pinch roller has the trend of being close to initiative rolling wheel or driven rolling wheel, guarantees to act as go-between and can be compressed tightly. The spring can be compressed, then the acting as go-between can pass through smoothly when the pinch roller, avoids the pinch roller to compress tightly the condition of acting as go-between.

As the preferred scheme of the utility model, the quantity of acting as go-between is four, four equipartitions of acting as go-between on the bottom circumference of isolated cloth. The stay wires are uniformly distributed on the bottom circular shaft of the isolation cloth, so that when the isolation cloth is put away or put down, all sides of the isolation cloth synchronously act, and the condition that the isolation cloth is not put away or hung by an aircraft engine is avoided.

The utility model has the advantages that:

the utility model discloses a rolling actuating mechanism can drive the rotation of initiative rolling wheel, and when initiative rolling wheel rotated, initiative rolling wheel passed through drive mechanism and drives driven rolling wheel and rotate. The active winding wheel and the driven winding wheel wind the stay wire out, so that the isolation cloth can hang down under the action of gravity and surround the aircraft engine. The gas nozzle sprays gas to the area between the isolation cloth and the aircraft engine, so that the concentration of fire extinguishing gas around the aircraft engine is quickly improved, and the aircraft engine is quickly extinguished. The isolation cloth can prevent the fire extinguishing gas from diffusing and ensure that the fire extinguishing gas forms a full-submerged environment around the aircraft engine.

Drawings

Fig. 1 is a schematic structural diagram of the present invention;

FIG. 2 is a partial block diagram of the present invention;

fig. 3 is a rear view of a partial structure.

In the figure, 1 — aircraft engine; 2-isolating cloth; 3-on the aircraft engine pylon; 4-a winding driving mechanism; 5, driving a winding wheel; 6, a driven winding wheel; 7-a transmission mechanism; 8-a stay wire; 9-a pinch roller; 21-a weight block; 31-a gas shower; 32-a chute; 33-a slide block; 34-a spring; 41-a motor; 42-a reducer; 71-a drive sprocket; 72-a driven sprocket; 73-a drive gear; 74-driven gear.

Detailed Description

Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present invention, and should not be construed as limiting the present invention.

As shown in fig. 1 and 2, the automatic covering and retracting gas fire extinguishing insulation device of the present embodiment includes an insulation cloth 2 for surrounding an aircraft engine 1, the insulation cloth 2 is cylindrical, the insulation cloth 2 is connected to an aircraft engine hanger 3, and a gas nozzle 31 is mounted on the aircraft engine hanger 3; the winding mechanism is characterized in that a winding driving mechanism 4 is installed on the aircraft engine hanger 3, an output end of the winding driving mechanism 4 is connected with a driving winding wheel 5, a plurality of driven winding wheels 6 are installed on the aircraft engine hanger 3, a transmission mechanism 7 is connected between the driving winding wheel 5 and the driven winding wheels 6, pull wires 8 are wound on the driving winding wheel 5 and the driven winding wheels 6, and the other ends of the pull wires 8 are connected with the lower end of the isolation cloth 2.

When the aircraft engine 1 fires in a test, the winding driving mechanism 4 is started, and the winding driving mechanism 4 drives the driving winding wheel 5 to rotate. When the driving winding wheel 5 rotates, the driving winding wheel 5 drives the driven winding wheel 6 to rotate through the transmission mechanism 7. The pull wire 8 is wound out by the driving winding wheel 5 and the driven winding wheel 6, so that the insulating cloth 2 can hang down under the action of gravity and surround the aircraft engine 1. The gas nozzle 31 injects gas to the area between the insulating cloth 2 and the aircraft engine 1, so that the concentration of the fire extinguishing gas around the aircraft engine 1 is rapidly increased, and the aircraft engine 1 is rapidly extinguished. The insulating cloth 2 can prevent the fire extinguishing gas from diffusing and ensure that the fire extinguishing gas forms a total flooding environment around the aircraft engine 1.

The gas in the gas source device can be carbon dioxide, heptafluoropropane, IG541 and other fire extinguishing gases. The gas source devices are respectively connected with the gas nozzles 31 through hoses. The gas shower 31 is arranged towards the aircraft engine 1. The gas nozzles 31 spray extinguishing gas against the aircraft engine 1, so that the surroundings of the aircraft engine 1 can be surrounded by extinguishing gas, thereby isolating oxygen and enabling the fire to be controlled.

Specifically, the winding driving mechanism 4 includes a motor 41, an output shaft of the motor 41 is connected to a speed reducer 42, the motor 41 and the speed reducer 42 are both mounted on the aircraft engine hanger 3, and the driving winding wheel 5 is connected to an output shaft of the speed reducer 42. After the motor 41 is started, the motor 41 drives the speed reducer 42 to act, the speed reducer 42 drives the driving winding wheel 5 to rotate, the driving winding wheel 5 can wind up or put down the pull wire 8 on the side, and the driving winding wheel 5 can drive the driven winding wheel 6 to rotate through the transmission mechanism 7.

Specifically, the transmission mechanism 7 comprises a driving sprocket 71, the driving sprocket 71 is connected to the driving take-up pulley 5, a driven sprocket 72 is connected to the aircraft engine hanger 3, the driving sprocket 71 and the driven sprocket 72 are connected through chain transmission, a driving gear 73 is connected to the driven sprocket 72, a driven gear 74 is connected to the driven take-up pulley 6, and the driving gear 73 is meshed with the driven gear 74. When the driving winding wheel 5 rotates, the driving sprocket 71 correspondingly rotates, and the driving sprocket 71 drives the driven sprocket 72 to rotate through the chain. When the driven sprocket 72 rotates, the driving gear 73 correspondingly rotates and drives the driven gear 74 to rotate. When the driven gear 74 rotates, the driven take-up wheel 6 correspondingly rotates and takes up or puts down the side wire 8. After transmission of the transmission mechanism 7, the driving winding wheel 5 and the driven winding wheel 6 are opposite in rotation direction, and all sides of the isolation cloth 2 are guaranteed to be simultaneously folded or simultaneously put down, so that control is convenient.

Furthermore, a weight block 21 is fixed at the lower end of the insulating cloth 2, and the pull wire 8 is connected to the position of the insulating cloth 2 connected with the weight block 21. The weight block 21 enables the isolated cloth 2 to be pulled down, so that the isolated cloth 2 can smoothly surround the aircraft engine 1, and the utility model discloses it is more reliable. The weight block 21 can also tighten the pull wire 8, so that the pull wire 8 can be accurately wound on the driving winding wheel 5 or the driven winding wheel 6, and the pull wire 8 is prevented from loosening.

Furthermore, a pressing wheel 9 for pressing the pull wire 8 is arranged beside each of the driving winding wheel 5 and the driven winding wheel 6. The pressing wheel 9 can compress the stay wire 8, so that the stay wire 8 is prevented from loosening on the driving winding wheel 5 or the driven winding wheel 6, and the reliability of the stay wire 8 for pulling the isolation cloth 2 is ensured.

The aircraft engine hanger 3 is provided with a sliding groove 32, a sliding block 33 is sleeved in the sliding groove 32, the pressing wheel 9 is rotatably connected to the sliding block 33, and a spring 34 is connected between the bottom of the sliding groove 32 and the sliding block 33. The spring 34 can push the sliding block 33 upwards, and the pressing wheel 9 has a tendency to be close to the driving winding wheel 5 or the driven winding wheel 6, so that the pull wire 8 can be pressed tightly. The spring 34 can be compressed, so that the pull wire 8 can pass through the pressing wheel 9 smoothly, and the situation that the pressing wheel 9 presses the pull wire 8 is avoided.

Furthermore, the number of the stay wires 8 is four, and the four stay wires 8 are uniformly distributed on the circumference of the bottom of the isolation cloth 2. The stay wires 8 are uniformly distributed on the bottom circular shaft of the isolation cloth 2, so that when the isolation cloth 2 is folded or put down, all sides of the isolation cloth 2 synchronously act, and the condition that the isolation cloth 2 is not folded or hung by the aircraft engine 1 is avoided.

The present invention is not limited to the above-mentioned optional embodiments, and any other products in various forms can be obtained by anyone under the teaching of the present invention, and any changes in the shape or structure thereof, all the technical solutions falling within the scope of the present invention, are within the protection scope of the present invention.

Claims

1. An isolation device for gas fire extinguishing capable of automatically covering and retracting is characterized by comprising isolation cloth (2) used for surrounding an aircraft engine (1), wherein the isolation cloth (2) is cylindrical, the isolation cloth (2) is connected to an aircraft engine hanger (3), and a gas spray head (31) is mounted on the aircraft engine hanger (3); install rolling actuating mechanism (4) on aircraft engine gallows (3), the output of rolling actuating mechanism (4) is connected with initiative rolling wheel (5), installs a plurality of driven rolling wheels (6) on aircraft engine gallows (3), is connected with drive mechanism (7) between initiative rolling wheel (5) and the driven rolling wheel (6), all winds on initiative rolling wheel (5) and driven rolling wheel (6) and is equipped with stay wire (8), and the other end and the lower extreme of isolated cloth (2) of stay wire (8) are connected.

2. The automatic covering and retracting type gas fire-extinguishing isolating device according to claim 1, wherein the winding driving mechanism (4) comprises a motor (41), an output shaft of the motor (41) is connected with a speed reducer (42), the motor (41) and the speed reducer (42) are both mounted on the aircraft engine hanger (3), and the driving winding wheel (5) is connected to an output shaft of the speed reducer (42).

3. The automatic covering and retracting type gas fire extinguishing insulation device according to claim 1, wherein the transmission mechanism (7) comprises a driving sprocket (71), the driving sprocket (71) is connected to the driving winding wheel (5), a driven sprocket (72) is connected to the aircraft engine hanger (3), the driving sprocket (71) and the driven sprocket (72) are connected through chain transmission, a driving gear (73) is connected to the driven sprocket (72), a driven gear (74) is connected to the driven winding wheel (6), and the driving gear (73) is meshed with the driven gear (74).

4. The automatic covering and retracting gas fire-extinguishing insulation device according to claim 1, wherein a weight block (21) is fixed to the lower end of the insulation cloth (2), and the stay (8) is connected to the insulation cloth (2) at a position where the weight block (21) is connected.

5. The automatic covering and retracting insulating device for gas fire extinguishing according to claim 1, wherein a pressing wheel (9) for pressing the stay wire (8) is provided beside each of the driving winding wheel (5) and the driven winding wheel (6).

6. The automatic covering and retracting type gas fire extinguishing isolation device according to claim 5, wherein a sliding groove (32) is formed in the aircraft engine hanger (3), a sliding block (33) is sleeved in the sliding groove (32), the pressing wheel (9) is rotatably connected to the sliding block (33), and a spring (34) is connected between the bottom of the sliding groove (32) and the sliding block (33).

7. The automatic covering and retracting type gas fire extinguishing insulation device according to any one of claims 1 to 6, wherein the number of the pull wires (8) is four, and the four pull wires (8) are uniformly distributed on the bottom circumference of the insulation cloth (2).