CN217366954U - Fire extinguishing system for engine compartment of double-engine aircraft - Google Patents
Fire extinguishing system for engine compartment of double-engine aircraft Download PDFInfo
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- CN217366954U CN217366954U CN202123316547.7U CN202123316547U CN217366954U CN 217366954 U CN217366954 U CN 217366954U CN 202123316547 U CN202123316547 U CN 202123316547U CN 217366954 U CN217366954 U CN 217366954U
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
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Abstract
The application belongs to the field of aircraft engines, and particularly relates to a fire extinguishing system for a double-engine aircraft engine cabin. Through setting up two fixed fire-extinguishing bottle, be used for the secondary after once putting out a fire and the after reburning in left and right engine compartment respectively and put out a fire, every fixed fire-extinguishing bottle disposes two fire-extinguishing bolt heads, is equipped with the electric explosion pipe on the fire-extinguishing bolt head, and two return circuit redundancy power supplies are carried out through two different emergent busbar to every electric explosion pipe. After the electric detonator is detonated, the fire extinguishing agent is released to the fire extinguishing pipeline from the bottle body through the corresponding fire extinguishing bolt head, the fire extinguishing pipeline connected with the fire extinguishing bolt heads on the two fire extinguishing bottles is connected to the fire extinguishing nozzles of the left engine room and the right engine room through the tee joint one-way valve in a cross mode, and the fire extinguishing nozzles spray to the corresponding engine rooms on fire so as to achieve the fire extinguishing effect. The two fire extinguishing bottles are cross-linked through the three-way check valve, can be connected to any engine compartment through a fire extinguishing pipeline, and have two-time spraying fire extinguishing capability for any one of a left engine compartment and a right engine compartment of a double-engine airplane.
Description
Technical Field
The application belongs to the field of aircraft engines, and particularly relates to a fire extinguishing system for a double-engine aircraft engine cabin.
Background
Fire hazards on board an aircraft are one of the most serious hazards that can occur. The combined configuration of various fire sources, high-temperature components and oil pipelines in an aircraft engine cabin can possibly cause fire, secondary fire can also possibly be caused due to damage of systems and pipelines in the cabin after the fire extinguishing agent is sprayed, and serious threats are generated to the safety of aircrew, passengers and airplanes. At present, a fire extinguishing bottle is mostly adopted in an engine compartment fire extinguishing system of a double-engine airplane, fire extinguishing spraying can be carried out on any engine compartment only once, and once the engine is re-ignited after fire extinguishing, unpredictable disasters can be brought.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
SUMMERY OF THE UTILITY MODEL
It is an object of the present application to provide a dual aircraft engine compartment fire suppression system to address at least one of the problems with the prior art.
The technical scheme of the application is as follows:
a dual engine aircraft engine compartment fire suppression system comprising:
the engine compartment comprises a left engine compartment and a right engine compartment, a left fire extinguishing nozzle is arranged in the left engine compartment, and a right fire extinguishing nozzle is arranged in the right engine compartment;
the fixed fire extinguishing bottle comprises a main fire extinguishing bottle and a spare fire extinguishing bottle, a left fire primary fire extinguishing bolt head and a right fire primary fire extinguishing bolt head are arranged on the main fire extinguishing bottle, and a left fire secondary fire extinguishing bolt head and a right fire secondary fire extinguishing bolt head are arranged on the spare fire extinguishing bottle;
the four electric explosion tubes are respectively arranged on the left fire primary fire hydrant head, the right fire primary fire hydrant head, the left fire secondary fire hydrant head and the right fire secondary fire hydrant head;
the fire extinguishing pipeline comprises a first fire extinguishing pipeline and a second fire extinguishing pipeline, one end of the first fire extinguishing pipeline is connected with the left fire primary fire extinguishing bolt head and the left fire secondary fire extinguishing bolt head respectively through a three-way check valve, the other end of the first fire extinguishing pipeline is connected with the left fire extinguishing nozzle, one end of the second fire extinguishing pipeline is connected with the right fire primary fire extinguishing bolt head and the right fire secondary fire extinguishing bolt head respectively through a three-way check valve, and the other end of the second fire extinguishing pipeline is connected with the right fire extinguishing nozzle;
the fire detector comprises a left fire detector and a right fire detector, the left fire detector is arranged in the left engine room, and the right fire detector is arranged in the right engine room;
and the fire extinguishing controller is used for controlling the electric detonator to detonate according to the received fire alarm signal of the fire detector.
In at least one embodiment of this application, the fire extinguishing controller is configured with the control panel of putting out a fire, be provided with left fire alarm lamp and right fire alarm lamp on the control panel of putting out a fire, left side fire alarm lamp is used for right the fire alarm signal of left side fire detector shows, right side fire alarm lamp is used for right the fire alarm signal of right side fire detector shows.
In at least one embodiment of this application, be provided with left fire extinguishing switch and right fire extinguishing switch on the control panel of putting out a fire, left side fire extinguishing switch and right side fire extinguishing switch is the tribit switch, normally is in neutral position, shifts to once the position of putting out a fire upwards, shifts to the secondary position of putting out a fire downwards.
In at least one embodiment of this application, all be provided with the visor that is used for preventing the mistake to bump on the switch that puts out a fire on a left side and the switch that puts out a fire on a right side.
In at least one embodiment of the present application, the fire suppression controller is provided with an electrical detonator detection module for detecting the electrical detonator.
In at least one embodiment of this application, be provided with electric detonator detection switch and electric detonator pilot lamp on the control panel of putting out a fire, electric detonator detection switch is two switches, normally is in the open position, and it is right to stir to detect the position upwards electric detonator detects, and the circuit is then normally corresponding electric detonator pilot lamp is bright.
Utility model has the following beneficial technical effects:
the utility model provides a two aircraft engine cabin fire extinguishing systems adopts the secondary injection system design to two aircraft engine cabins, can deal with the possibility of after putting out a fire in the engine cabin, promotes flight safety.
Drawings
FIG. 1 is a schematic view of a dual engine aircraft engine compartment fire suppression system according to an embodiment of the present application;
FIG. 2 is a schematic view of a fire suppression control panel according to one embodiment of the present application.
Wherein:
1-main fire extinguishing bottle; 2-fire extinguishing bolt head for one time; 3-right sending a primary fire hydrant head; 4-three-way one-way valve; 5-standby fire extinguishing bottles; 6-right secondary fire hydrant head; 7-a secondary fire hydrant head is arranged on the left; 8-fire extinguishing pipeline; 9-right fire extinguishing nozzle; 10-right engine compartment; 11-left fire extinguishing nozzle; 12-left engine compartment.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the accompanying drawings are illustrative and intended to explain the present application and should not be construed as limiting the present application. All other embodiments obtained by a person of ordinary skill in the art based on the embodiments in the present application without making any creative effort belong to the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.
The present application is described in further detail below with reference to fig. 1-2.
The application provides a two aircraft engine compartment fire extinguishing systems includes: engine room, fixed fire-extinguishing bottle, electric explosion tube, fire-extinguishing pipeline 8, fire detector and fire extinguishing controller.
Specifically, as shown in fig. 1, the engine compartment is a dual engine aircraft engine compartment, and includes a left engine compartment 12 and a right engine compartment 10, wherein a left fire extinguishing nozzle 11 is disposed in the left engine compartment 12, and a right fire extinguishing nozzle 9 is disposed in the right engine compartment 10.
Fixed fire bottle is including main fire bottle 1 and reserve fire bottle 5, there are two fire hydrant heads on every fixed fire bottle, wherein, be provided with the fire hydrant head 2 and the fire hydrant head 3 of sending out once in the right side of sending out once in the left side on the main fire bottle 1, be provided with the fire hydrant head 7 of sending out the secondary in the left side and send out the secondary in the right side on the reserve fire bottle 5 and put out a fire, can realize once putting out a fire through main fire bottle 1, after the fire-fighting after-combustion in engine compartment once, realize the secondary through reserve fire bottle 5 and put out a fire, promote flight safety.
The electric blasting cartridge includes four, and four electric blasting cartridges set up respectively on the left side sends out primary fire hydrant head 2, the right side sends out primary fire hydrant head 3, the left side sends out secondary fire hydrant head 7 and the right side sends out secondary fire hydrant head 6, and after the electric blasting cartridge was detonating, the fire extinguishing agent can be followed the fire hydrant head and released.
The fire detector includes left fire detector and right fire detector, and left fire detector sets up in left engine compartment 12, and right fire detector sets up in right engine compartment 10, realizes the detection of condition of a fire through setting up the fire detector in corresponding engine compartment, and the fire extinguishing controller can be according to the fire alarm signal of the fire detector who receives, and control electric detonator is detonating.
In a preferred embodiment of the application, the fire extinguishing controller is configured with a fire extinguishing control panel, and a left fire alarm lamp and a right fire alarm lamp are arranged on the fire extinguishing control panel, wherein the left fire alarm lamp is used for displaying the fire alarm signal of the left fire detector, the right fire alarm lamp is used for displaying the fire alarm signal of the right fire detector, and if an engine compartment on one side of the aircraft catches fire, the corresponding fire alarm lamp on the fire extinguishing control panel is turned on.
In this embodiment, be provided with on the control panel of putting out a fire left side and send out the switch of putting out a fire and the right side and send out the switch of putting out a fire, send out the switch of putting out a fire on a left side and send out the switch of putting out a fire on the right side and be the tribit switch, normally be in neutral position, stir the position of once putting out a fire upwards, stir the position of putting out a fire downwards to the secondary. The fire extinguishing switch on the fire extinguishing control panel can control the electric detonator through the control circuit, and the fire extinguishing agent is released from the fire hydrant head to enter the connected fire extinguishing pipeline 8 after the electric detonator is detonated. Advantageously, in this embodiment, protective covers may be disposed on both the left fire extinguishing switch and the right fire extinguishing switch to prevent accidental collisions.
In a preferred embodiment of the present application, the fire extinguishing controller is further provided with an electric detonator detection module for detecting an electric detonator. In this embodiment, be provided with electric detonator detection switch and electric detonator pilot lamp on the control panel of putting out a fire, electric detonator detection switch is two switches, normally is in the open position, and it detects to stir to detect the position to electric detonator upwards, and the electric detonator pilot lamp that the circuit normally then corresponds is bright.
The utility model provides a two aircraft engine cabin fire extinguishing systems, through setting up two fixed fire extinguishing bottle, be used for respectively the secondary after once putting out a fire and the after-combustion in left and right engine cabin to put out a fire, every fixed fire extinguishing bottle disposes two fire hydrant heads, is equipped with the electric detonator on the fire hydrant head, and every electric detonator carries out two return circuit redundancy power supplies through two different emergent busbar. After the electric detonator is detonated, the fire extinguishing agent is released to a fire extinguishing pipeline from the bottle body through the corresponding fire extinguishing bolt head, the fire extinguishing pipeline connected with the fire extinguishing bolt heads on the two fire extinguishing bottles is connected to fire extinguishing nozzles of the left engine room and the right engine room through the tee joint one-way valve in a crossed mode, and the fire extinguishing nozzles spray to the corresponding fire engine rooms to achieve the fire extinguishing effect. The two fire extinguishing bottles are cross-linked through the three-way check valve, can be connected to any engine compartment through a fire extinguishing pipeline, and have two-time spraying fire extinguishing capability for any one of a left engine compartment and a right engine compartment of a double-engine airplane.
The utility model provides a two aircraft engine cabin fire extinguishing systems adopts the secondary injection system design to two aircraft engine cabins, can deal with the possibility of after putting out a fire in the engine cabin, promotes flight safety.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (6)
1. A dual engine aircraft engine compartment fire suppression system, comprising:
the engine compartment comprises a left engine compartment (12) and a right engine compartment (10), wherein a left fire extinguishing nozzle (11) is arranged in the left engine compartment (12), and a right fire extinguishing nozzle (9) is arranged in the right engine compartment (10);
the fixed fire extinguishing bottle comprises a main fire extinguishing bottle (1) and a standby fire extinguishing bottle (5), wherein a left primary fire extinguishing bolt head (2) and a right primary fire extinguishing bolt head (3) are arranged on the main fire extinguishing bottle (1), and a left secondary fire extinguishing bolt head (7) and a right secondary fire extinguishing bolt head (6) are arranged on the standby fire extinguishing bottle (5);
the four electric explosion tubes are respectively arranged on the left fire primary fire extinguishing bolt head (2), the right fire primary fire extinguishing bolt head (3), the left fire secondary fire extinguishing bolt head (7) and the right fire secondary fire extinguishing bolt head (6);
the fire extinguishing pipeline (8) comprises a first fire extinguishing pipeline and a second fire extinguishing pipeline, one end of the first fire extinguishing pipeline is connected with the left fire primary fire extinguishing bolt head (2) and the left fire secondary fire extinguishing bolt head (7) through a three-way check valve (4) respectively, the other end of the first fire extinguishing pipeline is connected with the left fire extinguishing nozzle (11), one end of the second fire extinguishing pipeline is connected with the right fire primary fire extinguishing bolt head (3) and the right fire secondary fire extinguishing bolt head (6) through a three-way check valve (4) respectively, and the other end of the second fire extinguishing pipeline is connected with the right fire extinguishing nozzle (9);
the fire detector comprises a left fire detector and a right fire detector, the left fire detector is arranged in the left engine compartment (12), and the right fire detector is arranged in the right engine compartment (10);
and the fire extinguishing controller is used for controlling the electric detonator to detonate according to the received fire alarm signal of the fire alarm detector.
2. The dual aircraft engine compartment fire extinguishing system according to claim 1, wherein the fire extinguishing controller is configured with a fire extinguishing control panel on which a left fire alarm lamp and a right fire alarm lamp are provided, the left fire alarm lamp being configured to display the fire alarm signal of the left fire detector, and the right fire alarm lamp being configured to display the fire alarm signal of the right fire detector.
3. The dual-engine aircraft engine compartment fire suppression system of claim 2, wherein the fire suppression control panel is provided with a left-fire suppression switch and a right-fire suppression switch, both of which are three-position switches, normally in a neutral position, shifted up to a primary fire suppression position, and shifted down to a secondary fire suppression position.
4. The dual aircraft engine compartment fire suppression system of claim 3, wherein a protective cover for preventing accidental impact is provided on each of the left fire switch and the right fire switch.
5. The dual engine aircraft engine compartment fire suppression system of claim 1, wherein the fire suppression controller is provided with an electrical squib detection module for detecting the electrical squib.
6. The dual-engine aircraft engine compartment fire extinguishing system according to claim 2, wherein the fire extinguishing control panel is provided with an electric detonator detection switch and an electric detonator indicator light, the electric detonator detection switch is a two-position switch, and is normally in an off position, and when the electric detonator detection switch is moved up to a detection position, the electric detonator is detected, and when the circuit is normal, the corresponding electric detonator indicator light is turned on.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202123316547.7U CN217366954U (en) | 2021-12-27 | 2021-12-27 | Fire extinguishing system for engine compartment of double-engine aircraft |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202123316547.7U CN217366954U (en) | 2021-12-27 | 2021-12-27 | Fire extinguishing system for engine compartment of double-engine aircraft |
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| CN217366954U true CN217366954U (en) | 2022-09-06 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202123316547.7U Active CN217366954U (en) | 2021-12-27 | 2021-12-27 | Fire extinguishing system for engine compartment of double-engine aircraft |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115845290A (en) * | 2022-12-27 | 2023-03-28 | 中国航空工业集团公司西安飞机设计研究所 | Fire extinguishing pipe network for engine compartment |
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2021
- 2021-12-27 CN CN202123316547.7U patent/CN217366954U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115845290A (en) * | 2022-12-27 | 2023-03-28 | 中国航空工业集团公司西安飞机设计研究所 | Fire extinguishing pipe network for engine compartment |
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