Aircraft engine fire bottle

Abstract

The utility model provides an aero-engine fire extinguishing bottle relates to aviation fire extinguishing bottle technical field, including bottle body, nozzle assembly, safety valve subassembly and low pressure pressure switch, bottle body fixedly connected with nozzle assembly, bottle body fixedly connected with safety valve subassembly, bottle body fixedly connected with low pressure pressure switch subassembly, bottle body has stainless steel inner layer and composite material outer layer, is equipped with the net -like bushing of bottomless bowl structure in nozzle assembly, the net -like bushing is equipped with through -hole equally, pass through the net -like bushing as first mechanical buffer layer, effective absorption of energy, can reduce initial injection velocity, avoid high -speed jet flow to the secondary damage of engine parts, through to the other structure of bottle body optimization, has promoted the strength of bottle body, realizes light weight, has promoted the reliability and durability of product, in the enhancement bottle body pressure -bearing capacity's time, reduce product weight, solve the problem of fire extinguishing agent corrosion leakage, improve product life cycle.

Description

Technical Field

[0001] This utility model relates to the field of aviation fire extinguishing bottle technology, specifically to an aircraft engine fire extinguishing bottle. Background Technology

[0002] Fire extinguishing bottles for aircraft engines are crucial equipment for ensuring flight safety. Their performance directly affects the effectiveness of extinguishing fires in the engine compartment and the overall safety of the aircraft.

[0003] Currently, most engine fire extinguishing bottles used in civil aircraft engine compartments are made of 1.8 mm alloy structural steel. As the service life increases, they are corroded by the fire extinguishing agent, resulting in corrosion and weld leakage. In addition, in order to ensure their pressure resistance, their heat treatment process has high requirements.

[0004] To ensure the pressure resistance of the bottle, the thickness of the material needs to be increased when the bottle is made of stainless steel, which leads to a significant increase in the weight of the bottle. This makes it impossible to meet the strict requirements for lightweighting in the aviation industry and affects fuel economy, especially for large engines that require multiple fire extinguishing bottles.

[0005] Aluminum alloy inner liner cylinders, which are sometimes made with composite metal winding, have low pressure resistance, and the thick composite material layer makes them unsuitable for cylinders with multiple interfaces. Plastic-lined gas cylinders, on the other hand, have low pressure resistance, are prone to leakage, and have a complex molding process.

[0006] Meanwhile, when existing aircraft engine fire extinguishing bottles detonate, the high-speed jet of extinguishing agent can easily cause secondary damage to engine components.

[0007] Chinese utility model patent CN203694461U discloses a novel self-starting fire extinguishing bottle, comprising: a bottle body, an outlet, a rupture membrane, and an electric detonator. The outlet is fitted onto the bottle body, the rupture membrane is disposed on the bottle body, and the electric detonator is disposed on the outlet, positioned above the rupture membrane. This novel self-starting fire extinguishing bottle improves the sealing performance of the fire extinguishing bottle and solves the problem of daily leakage. However, this design generates a high pressure of extinguishing agent spray when the fire extinguishing bottle detonates, which could easily cause secondary damage to aircraft engines.

[0008] Therefore, there is an urgent need to develop a fire extinguishing bottle for aircraft engines to solve the above problems. Utility Model Content

[0009] This utility model relates to a fire extinguishing bottle for aircraft engines. By integrating the air supply pump body and various control valves, and installing the air supply pump body components inside the valve plate unit, a high degree of integration of the air supply pump body and various control valves is achieved. Through the design of the gas pipeline, the gas is in an internal circulation mode, which improves the gas utilization rate, reduces energy consumption, and effectively solves the above-mentioned technical problems.

[0010] To achieve the above objectives, this utility model is implemented through the following technical solution: an aircraft engine fire extinguishing bottle, comprising a bottle body, a nozzle assembly, a safety valve assembly, and a low-pressure switch, wherein the nozzle assembly is fixedly connected to the bottle body, the safety valve assembly is fixedly connected to the bottle body, and the low-pressure switch assembly is fixedly connected to the bottle body, and the bottle body has a stainless steel inner layer and a composite material outer layer.

[0011] Preferably, the bottle body has a support leg at the bottom, the bottle body is filled with fire extinguishing agent, the bottle body has a safety valve interface on one side of the support leg, the bottle body has a pressure switch interface at the top, and the bottle body has a nozzle interface in the middle.

[0012] Preferably, the nozzle assembly includes: a nozzle elbow, a mesh bushing, a connecting sleeve, an elbow back cap, an elbow seal, a nozzle diaphragm, an inner diaphragm sealing gasket, and an outer diaphragm sealing ring. The nozzle interface has an inner diaphragm sealing gasket at its top, a nozzle diaphragm outside the inner diaphragm sealing gasket, and an outer diaphragm sealing ring outside the nozzle diaphragm. The connecting sleeve is bolted to the nozzle interface, clamping and fixing the nozzle diaphragm, inner diaphragm sealing gasket, and outer diaphragm sealing ring. The nozzle elbow is bolted to the connecting sleeve, a mesh bushing is provided between the nozzle elbow and the connecting sleeve, the elbow back cap is bolted to the nozzle elbow, and an elbow seal is provided between the elbow back cap and the connecting sleeve.

[0013] Preferably, the nozzle bend has an "L" shaped structure, the nozzle bend has a hollow structure, the top of the nozzle bend is provided with a threaded post, and one side of the nozzle bend is provided with a spray port.

[0014] Preferably, the mesh bushing has a bottomless bowl-shaped structure, and the mesh bushing has through holes at equal intervals.

[0015] Preferably, the safety component includes: a safety valve body, a safety valve diaphragm, a diaphragm gland, an O-ring, and a dust plug. The diaphragm gland is located below the safety valve body, and the safety valve diaphragm is located between the safety valve body and the diaphragm gland. The safety valve body is bolted to the safety valve interface, and an O-ring is located between the safety valve body and the safety valve interface. A dust plug is bolted to the top of the safety valve body.

[0016] Preferably, the low-pressure switch includes: a housing, a socket, a cover plate, a base connecting tube, a micro switch, and a switch connector. The socket is located below the housing. The base connecting tube and the micro switch are located inside the housing. The base connecting tube is electrically connected to the flavor plate switch and to the socket. The switch connector is located on one side of the housing, and the cover plate is located on the other side of the housing.

[0017] Preferably, the base connecting end tube includes a C-shaped end tube, a connector post, a copper tube, and a cap. One side of the connector post is fixedly connected to the connector post, and the other side of the C-shaped end tube is fixedly connected to the cap. A copper tube is provided inside the C-shaped end tube, and the connector post and the cap are fixedly connected to the shell.

[0018] Preferably, the micro switch has a low-pressure alarm function, and when the pressure inside the fire extinguisher bottle reaches the low-pressure switch set value, the micro switch sends an alarm signal.

[0019] Preferably, the outer layer of the composite material is a 0.6mm carbon fiber composite material, and the inner stainless steel layer is a 1mm thick duplex stainless steel material.

[0020] Beneficial effects

[0021] This utility model provides a fire extinguishing bottle for aircraft engines, which has the following advantages compared with the existing technology:

[0022] This utility model uses a double-layer composite structure to make the bottle body. The inner layer uses duplex stainless steel as the inner liner, which can weld various joints and ensure corrosion resistance. The outer layer uses carbon fiber prepreg material, which is manually laid and then cured at high temperature to improve the overall strength. This avoids the leakage problem of simple steel gas cylinders, reduces the weight of the bottle body, and improves the pressure bearing capacity of the bottle body.

[0023] This utility model features a nozzle interface, a safety valve interface, and a pressure switch interface on the bottle body. Through optimized layout and connection methods, it ensures the reliability of extinguishing agent spraying and ease of operation. The safety valve assembly serves as both a filling interface and a safety venting function, achieving "multi-purpose use in one port." When the pressure inside the bottle is abnormal, the safety valve diaphragm will rupture, releasing the extinguishing agent and preventing the bottle from exploding and damaging the aircraft. The low-pressure switch is connected to the alarm system; when the extinguishing bottle leaks and the pressure falls below the set value, the switch will trigger an alarm signal, alerting the pilot to address the malfunction promptly and improving flight safety.

[0024] This invention uses a mesh bushing as the first mechanical buffer layer to effectively absorb the energy of the propellant, reduce the initial injection speed, and avoid secondary damage to engine components from the high-speed jet.

[0025] This utility model is used for storing fire extinguishing agents and extinguishing engine compartment fires. By optimizing the structure of the fire extinguishing agent storage bottle, the strength of the bottle is improved, the weight is reduced, the reliability and durability of the product are enhanced, the pressure-bearing capacity of the bottle is increased, the weight of the product is reduced, the problem of corrosion and leakage of fire extinguishing agents is solved, and the product life cycle is extended. Attached Figure Description

[0026] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on the provided drawings without creative effort.

[0027] Figure 1 This is a schematic diagram of the device structure of this utility model;

[0028] Figure 2 This is a side view of the device of this utility model;

[0029] Figure 3 This is a schematic diagram of the bottle structure of this utility model;

[0030] Figure 4 This is a cross-sectional view of the nozzle assembly of this utility model in its connected state;

[0031] Figure 5 This is a schematic diagram of the mesh bushing structure of this utility model;

[0032] Figure 6 This is a top view of the low-pressure switch of this utility model;

[0033] Figure 7 This is a vertical sectional view of the low-pressure switch of this utility model;

[0034] Figure 8 This is a schematic diagram of the base connecting end tube structure of this utility model;

[0035] In the picture:

[0036] 1. Bottle body; 101. Stainless steel inner layer; 102. Composite material outer layer; 103. Support leg; 104. Safety valve interface; 105. Pressure switch interface; 106. Nozzle interface.

[0037] 2. Nozzle assembly; 201. Nozzle elbow; 2011. Threaded post; 2012. Injection port; 202. Mesh bushing; 2021. Through hole; 203. Connecting sleeve; 204. Elbow back cap; 205. Elbow seal; 206. Nozzle diaphragm; 207. Inner diaphragm gasket; 208. Outer diaphragm sealing ring.

[0038] 3. Safety valve assembly, 301. Safety valve body, 302. Safety valve diaphragm, 303. Diaphragm gland, 304. O-ring, 305. Dust plug.

[0039] 4. Low-voltage pressure switch; 401. Housing; 402. Socket; 403. Cover plate; 404. Base connecting tube; 4041. C-type connecting tube; 4042. Connector post; 4043. Copper tube; 4044. Head; 405. Micro switch; 406. Switch connector.

[0040] 5. Locking thread, 6. Lead seal, 7. Signage. Detailed Implementation

[0041] To make the technical problems, technical solutions and beneficial effects of this utility model clearer, this utility model will be further described in detail with reference to the embodiments and accompanying drawings. It should be understood that the specific embodiments described herein are only used to explain this utility model and are not intended to limit this utility model. The technical solutions of this utility model will be described in detail below with reference to the embodiments and accompanying drawings, but the scope of protection is not limited thereto.

[0042] Please see Figure 1-8 This utility model provides a technical solution:

[0043] An aircraft engine fire extinguishing bottle includes a bottle body 1, a nozzle assembly 2, a safety valve assembly 3, and a low-pressure switch 4. The nozzle assembly 2 is fixedly connected to the middle of the bottle body 1, the safety valve assembly 3 is fixedly connected to the lower part of the bottle body 1, and the low-pressure switch 4 assembly is fixedly connected to the upper part of the bottle body 1. The bottle body 1 has a stainless steel inner layer 101 and a composite material outer layer 102.

[0044] In some embodiments, the bottle body 1 has a support leg 103 at the bottom, the support leg 103 adopts a triangular distribution support structure to make the bottle body stable. The bottle body 1 contains a fire extinguishing agent. The bottle body 1 has a safety valve interface 104 on one side of the support leg 103. The safety valve interface 104 is bolted to the safety valve assembly 3. The bottle body 1 has a pressure switch interface 105 at the top, the pressure switch interface 105 is bolted to the low pressure switch 4. The bottle body 1 has a nozzle interface 106 in the middle, the nozzle interface 106 is bolted to the spray assembly.

[0045] In some embodiments, the bottle body 1 is the main body of the fire extinguishing bottle used to contain the extinguishing agent. To reduce the overall weight of the product and improve its reliability, the bottle body 1 adopts a double-layer composite structure. The stainless steel inner layer 101 is made of a hollow sphere of duplex stainless steel with a thickness of 1mm. While providing support for the outer layer, it can also bear some pressure, solving the problem of connecting various metal joints with the composite material. The composite material outer layer 102 is made of carbon fiber composite material with a thickness of 0.6mm, which improves the overall compressive strength of the product while reducing its weight.

[0046] In some embodiments, two sets of nozzle assemblies 2 are provided on the bottle body 1 to increase the stability of fire suppression for aircraft engines.

[0047] In some embodiments, the nozzle assembly 2 includes: a nozzle elbow 201, a mesh bushing 202, a connecting sleeve 203, an elbow back cap 204, an elbow seal 205, a nozzle diaphragm 206, an inner diaphragm sealing gasket 207, and an outer diaphragm sealing ring 208. The nozzle interface 106 has an inner diaphragm sealing gasket 207 at its top, a nozzle diaphragm 206 on its outer side, and an outer diaphragm sealing ring 208 on its outer side. The connecting sleeve 203 is bolted to the nozzle interface 106 and clamps and fixes the nozzle diaphragm 206, the inner diaphragm sealing gasket 207, and the outer diaphragm sealing ring 208. The inner diaphragm sealing gasket 207 and the outer diaphragm sealing ring 208 provide support and protection for the nozzle diaphragm 206.

[0048] The nozzle elbow 201 is bolted to the connecting sleeve 203. A mesh bushing 202 is provided between the nozzle elbow 201 and the connecting sleeve 203. The elbow back cap 204 is bolted to the nozzle elbow 201. An elbow seal 205 is provided between the elbow back cap 204 and the connecting sleeve 203.

[0049] In some embodiments, the inner sealing gasket 207 of the diaphragm is made of copper, and the outer sealing ring 208 of the diaphragm is made of stainless steel.

[0050] In some embodiments, the nozzle elbow 201 has an "L" shaped structure and a hollow structure. The top of the nozzle elbow 201 is provided with a threaded post head 2011, and a spray port 2012 is provided on one side of the nozzle elbow 201. The spray port 2012 is connected to the aircraft pipeline. When the explosion cap detonates and penetrates the nozzle diaphragm 206, the nozzle assembly 2 acts as a channel for the spraying of the extinguishing agent.

[0051] In some embodiments, the mesh bushing 202 has a bottomless bowl-shaped structure. The mesh bushing 202 is provided with through holes 2021 at equal intervals, and the diameter of the through holes 2021 gradually decreases from top to bottom. The distribution density of the through holes 2021 is optimized by hydrodynamics to ensure that a uniform vortex is formed when the extinguishing agent passes through. When the mesh bushing 202 is installed, the opening direction faces the nozzle diaphragm 206. The bottom diameter of the mesh bushing 202 corresponds to the diameter of the spray port 2012, and the upper part of the mesh bushing 202 corresponds to the inner diameter of one side of the nozzle elbow 201. The mesh bushing 202 perfectly fits the internal space contour of the nozzle assembly 2.

[0052] When the explosive cap detonates, the mesh bushing 202 acts as the first mechanical buffer layer, effectively absorbing the energy of the propellant, reducing the initial injection velocity, and preventing secondary damage to engine components from the high-speed jet.

[0053] In some embodiments, the mesh bushing 202 is made of a lightweight composite material.

[0054] In some embodiments, the mesh bushing 202 is made of aluminum.

[0055] In some embodiments, the safety components include: a safety valve body 301, a safety valve diaphragm 302, a diaphragm cap 303, an O-ring 304, and a dust plug 305. The diaphragm cap 303 is located below the safety valve body 301, and the safety valve diaphragm 302 is located between the safety valve body 301 and the diaphragm cap 303. The diaphragm cap 303 wraps and clamps the bottom of the safety valve body 301. The safety valve body 301 is bolted to the safety valve interface 104, and an O-ring 304 is located between the safety valve body 301 and the safety valve interface 104. A dust plug 305 is bolted to the top of the safety valve body 301.

[0056] The safety component serves as the channel for injecting extinguishing agent. When there is a certain gap between the inner end of the safety valve and the bottom of the safety valve connector hole, extinguishing agent can be injected into the fire extinguishing bottle through the threaded hole on the exposed end of the safety valve. When the amount of extinguishing agent injected meets the requirements, continuing to turn the safety valve will ensure that its inner end face is in complete and secure contact with the bottom of the safety valve connector hole, thereby locking the injection channel. When the internal pressure of the fire extinguishing bottle becomes abnormal, the safety valve diaphragm 302 will be ruptured under the action of the internal pressure of the fire extinguishing bottle, releasing the extinguishing agent and thus preventing the fire extinguishing bottle from exploding due to internal high pressure and causing damage to the aircraft.

[0057] In some embodiments, the low-pressure switch 4 includes: a housing 401, a socket 402, a cover plate 403, a base connecting tube 404, a micro switch 405, and a switch connector 406. The socket 402 is located below the housing 401 and is connected to the aircraft alarm system. The base connecting tube 404 and the micro switch 405 are located inside the housing 401. The base connecting tube 404 is electrically connected to the odor control switch and the socket 402. The switch connector 406 is located on one side of the housing 401 and is bolted to the fire extinguishing bottle. The fire extinguishing bottle is connected to the low-pressure switch 4 through the central hole of the switch connector 406. The low-pressure switch 4 monitors the pressure inside the fire extinguishing bottle. The cover plate 403 is located above the housing 401. The upper edge of the housing 401 is threaded and the cover plate 403 is bolted to the housing 401. The outer side of the housing 401 is coated with black polyester amino orange-patterned baking paint.

[0058] In some embodiments, the base connecting end tube 404 includes a C-shaped end tube 4041, a connector post 4042, a copper tube 4043, and a cap 4044. One side of the connector post 4042 is fixedly connected to the connector post 4042, and the other side of the C-shaped end tube 4041 is fixedly connected to the cap 4044. The copper tube 4043 is provided inside the C-shaped end tube 4041. The connector post 4042 and the cap 4044 are fixedly connected to the housing 401. The base connecting end tube 404 provides a mechanical interface. The C-shaped end tube 4041 acts as a sensitive element to sense the system pressure and linearly outputs it as end displacement.

[0059] In some embodiments, the present invention reduces weight by 10%, increases bearing pressure by 15%, and extends product lifespan by 50% while maintaining the same extinguishing agent volume.

[0060] During storage, the nozzle assembly 2 is secured using a locking wire 5 and a lead seal 6. A label 7 is provided on one side of the aviation fire extinguishing bottle.

[0061] This aviation fire extinguishing bottle has undergone tests including water pressure, air pressure, explosion, impact, fatigue, low pressure alarm, safety valve, temperature-altitude, temperature change, impact, vibration, electromagnetic compatibility, salt spray, and mold, and has obtained the Civil Aviation Administration's approval release certificate.

[0062] The above description is a further detailed explanation of the present invention in conjunction with specific preferred embodiments. For those skilled in the art to which the present invention pertains, several simple deductions or substitutions can be made without departing from the present invention, and all such deductions or substitutions should be considered as falling within the scope of patent protection determined by the submitted claims.

Claims

1. A fire extinguishing bottle for aircraft engines, comprising a bottle body, a nozzle assembly, a safety valve assembly, and a low-pressure switch, characterized in that, The bottle body is fixedly connected to a nozzle assembly, a safety valve assembly, and a low-pressure switch assembly. The bottle body has a stainless steel inner layer and a composite material outer layer. The nozzle assembly includes: a nozzle elbow, a mesh bushing, a connecting sleeve, an elbow back cap, an elbow seal, a nozzle diaphragm, an inner diaphragm sealing gasket, and an outer diaphragm sealing ring. An inner diaphragm sealing gasket is located at the top of the nozzle interface. The nozzle diaphragm is located outside the inner diaphragm sealing gasket, and an outer diaphragm sealing ring is located outside the nozzle diaphragm. The connecting sleeve is bolted to the nozzle interface, clamping and fixing the nozzle diaphragm, the inner diaphragm sealing gasket, and the outer diaphragm sealing ring. The nozzle elbow is bolted to the connecting sleeve, and a mesh bushing is located between the nozzle elbow and the connecting sleeve. The elbow back cap is bolted to the nozzle elbow, and an elbow seal is located between the elbow back cap and the connecting sleeve.

2. The aircraft engine fire extinguishing bottle according to claim 1, characterized in that: The bottle has a support leg at the bottom, the bottle contains a fire extinguishing agent, the bottle has a safety valve interface on one side of the support leg, a pressure switch interface on the top of the bottle, and a nozzle interface in the middle of the bottle.

3. The aircraft engine fire extinguishing bottle according to claim 1, characterized in that: The nozzle bend has an "L" shaped structure and a hollow structure. The top of the nozzle bend is provided with a threaded post, and a spray port is provided on one side of the nozzle bend.

4. The aircraft engine fire extinguishing bottle according to claim 3, characterized in that: The mesh bushing has a bottomless bowl-shaped structure, and the mesh bushing has through holes at equal intervals.

5. The aircraft engine fire extinguishing bottle according to claim 1, characterized in that: The safety valve assembly includes: a safety valve body, a safety valve diaphragm, a diaphragm gland, an O-ring, and a dust plug. The diaphragm gland is located below the safety valve body, and the safety valve diaphragm is located between the safety valve body and the diaphragm gland. The safety valve body is bolted to the safety valve interface, and an O-ring is located between the safety valve body and the safety valve interface. A dust plug is bolted to the top of the safety valve body.

6. The aircraft engine fire extinguishing bottle according to claim 1, characterized in that: The low-pressure switch includes: a housing, a socket, a cover plate, a base connecting tube, a micro switch, and a switch connector. The socket is located below the housing. The base connecting tube and the micro switch are located inside the housing. The base connecting tube is electrically connected to the flavor plate switch and to the socket. The switch connector is located on one side of the housing, and the cover plate is located on the other side of the housing.

7. The aircraft engine fire extinguishing bottle according to claim 6, characterized in that: The base connecting end tube includes a C-shaped end tube, a connector post, a copper tube, and an end cap. One side of the connector post is fixedly connected to the connector post, and the other side of the C-shaped end tube is fixedly connected to the end cap. A copper tube is installed inside the C-shaped end tube, and the connector post and the end cap are fixedly connected to the shell.

8. The aircraft engine fire extinguishing bottle according to claim 6, characterized in that: The micro switch has a low-pressure alarm function. When the pressure inside the fire extinguisher bottle reaches the low-pressure switch set value, the micro switch sends an alarm signal.

9. The aircraft engine fire extinguishing bottle according to any one of claims 1-8, characterized in that: The outer layer of the composite material is a 0.6mm carbon fiber composite material, and the inner stainless steel layer is a 1mm thick duplex stainless steel metal material.

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