阅读说明：本技术 包括推进组件和用于推进组件的灭火系统的飞行器 (Aircraft comprising a propulsion assembly and a fire suppression system for the propulsion assembly ) 是由 蒂埃里·克拉韦尔 斯特凡·皮列塞 阿诺·吉绍 尼古拉·布拉谢 于 2021-05-11 设计创作，主要内容包括：本发明涉及一种飞行器,其包括推进组件和其灭火系统,灭火系统包括两个灭火剂储器、与每个储器相关联的控制件以及检测组件,控制件由飞行员致动以打开储器,检测组件检测起火并且如果合适的话发出起火警告信号,推进组件包括第一隔室和第二隔室,每个隔室包括至少一个起火区,灭火系统包括由定位单元控制的旁通阀、通过旁通阀将每个储器连接至每一个起火区的一组管道,定位单元检测第一隔室中的起火区中的起火并且如果合适的话控制旁通阀使得旁通阀采用第一状态,否则采用第二状态,在第一状态下,在启用控制件之后,储器中的灭火剂朝向第一隔室中的起火区排出,在第二状态下,在启用控制件之后,储器中的灭火剂朝向第二隔室中的起火区排出。(The invention relates to an aircraft comprising a propulsion assembly and a fire extinguishing system thereof, the fire extinguishing system comprising two reservoirs of fire extinguishing agent, a control associated with each reservoir, actuated by a pilot to open the reservoir, and a detection assembly to detect a fire and, if appropriate, to issue a fire warning signal, the propulsion assembly comprising a first compartment and a second compartment, each compartment comprising at least one fire zone, the fire extinguishing system comprising a bypass valve controlled by a positioning unit, a set of conduits connecting each reservoir to each fire zone through the bypass valve, the positioning unit detecting the fire in the fire zone in the first compartment and, if appropriate, controlling the bypass valve so that the bypass valve adopts a first state, in which, after activation of the control, the fire extinguishing agent in the reservoir is discharged towards the fire zone in the first compartment, in a second state, after activation of the control, the fire suppressant in the reservoir is expelled towards the fire area in the second compartment.)

1. An aircraft (a) comprising a cockpit, at least one propulsion assembly (10) and a Fire extinguishing system (20) dedicated to each propulsion assembly, each Fire extinguishing system (20) comprising two reservoirs (R1, R2), a control (C1, C2) associated with each reservoir (R1, R2) and a detection assembly (21), each reservoir containing a Fire extinguishing agent, said control being actuatable by a pilot to open the reservoir in order to release the Fire extinguishing agent therefrom, the detection assembly being configured to detect a Fire in the propulsion assembly (10) to which the Fire extinguishing system (20) is dedicated and, if appropriate, to issue a Fire warning signal (S _ Fire) intended for a visual or audible transducer (25) located in the cockpit, characterized in that the propulsion assembly (10) comprises a first and a second compartment (K1, b) and, K2) -each compartment comprising at least one ignition zone (Z1, Z2), and characterized in that the fire extinguishing system (20) comprises a bypass valve (26) controlled by a positioning unit (27), a set of conduits connecting each reservoir (R1, R2) to each of the ignition zones (Z1, Z2) through the bypass valve (26), the positioning unit (27) being configured to detect an ignition in the one or more ignition zones (Z1, Z2) in the first compartment (K1) and, if appropriate, to control the bypass valve (26) such that it adopts a first state, called controlled state, in which the reservoir (R1) is activated after activation of the C1, C2) associated with reservoir (R1, R2), r2) towards the one or more fire zones in the first compartment (K1), and in the second state, after activation of the control (C1, C2) associated with a reservoir (R1, R2), the fire-extinguishing agent in the reservoir (R1, R2) is discharged towards the fire zone of the second compartment (K2).

2. The aircraft (a) according to claim 1, characterised in that the bypass valve (26) comprises an inlet (26a) connected to each of the reservoirs (R1, R2), and two outlets (26b, 26c), wherein a first outlet (26b) is connected to the conduit leading into the one or more ignition zones (Z1, Z2) in the first compartment (K1), and a second outlet (26c) is connected to the conduit leading into the one or more ignition zones (Z1, Z2) in the second compartment (K2).

3. The aircraft (A) according to any one of claims 1 and 2, characterised in that the detection assembly (21) comprises a detection unit (22) to which a plurality of detection circuits (L) are connected, wherein each detection circuit (L) comprises at least one portion dedicated to each of the ignition zones (Z1, Z2) in the propulsion assembly (10), and wherein each portion comprises at least one ignition sensor (23, 24).

4. The aircraft (A) according to claim 3, characterised in that the detection unit (22) is configured to measure the electrical values of the circuit formed by each of the detection circuits (L) and to issue a warning signal (S _ Fire) if the measured values have values indicative of a Fire.

5. The aircraft (A) according to any one of claims 3 and 4, characterised in that the positioning unit (27) is electrically connected to the portion or portions of the detection circuit (L) dedicated to the ignition zone (Z1, Z2) in the first compartment (K1).

6. The aircraft (A) according to claim 5, characterized in that the positioning unit (27) is configured to measure the electrical value of the electrical circuit formed by the one or more portions of the detection circuit (L) dedicated to the ignition zone (Z1, Z2) in the first compartment (K1) and to send a control signal (S _ Com) to the bypass valve (26) to control the valve (26) so that it adopts its controlled state if said signal has a value indicating an ignition in the first compartment (K1).

7. The aircraft (A) according to claim 4 or claim 6, characterised in that the electrical value is a resistance.

Technical Field

The invention relates to an aircraft comprising a propulsion assembly and a fire extinguishing system dedicated to said propulsion assembly for detecting and extinguishing fires that may occur in the propulsion assembly.

Background

In a known manner, an aircraft has at least one propulsion assembly fastened under each of its wings and a fire extinguishing system dedicated to each propulsion assembly, which makes it possible to detect the occurrence of a fire in the propulsion assembly and to extinguish the fire.

Fig. 1 is a schematic representation of a prior art fire suppression system 1 dedicated to a propulsion assembly 2. The propulsion assembly 2 comprises a plurality of fire zones Z1, Z2 of different sizes, which are closed by walls and fire seals in order to prevent fire from spreading out of the fire zones and thus also from spreading from one fire zone to the other.

In each of the fire zones Z1, Z2, the fire extinguishing system 1 comprises at least one detection circuit 3 equipped with at least one fire sensor for detecting a fire. All detection circuits 3 are electrically connected to a detection unit 4 configured to trigger an audible or visual fire alarm intended for the pilot in the cockpit in the case of a fire detected by the fire sensors of the fire zones Z1, Z2.

After having triggered the fire alarm, the pilot follows a procedure which causes him or her to actuate the first control C1 located in the cockpit to trigger the discharge of a volume of extinguishing agent contained in the first reservoir R1 towards each of the fire zones Z1, Z2. If the fire continues, the pilot actuates a second control C2 located in the cockpit to repeat the same action, but this time using a second reservoir R2.

Depending on the design, each reservoir R1, R2 contains a volume of fire suppressant necessary to supply all the fire zones Z1, Z2 with sufficient fire suppressant to extinguish the fire therein, since the detection unit 4 is not able to detect exactly which fire zone Z1, Z2 fires.

Such fire suppression systems are entirely satisfactory, however, the reduced mass and/or volume requirements prevailing in aircraft construction render it necessary to find fire suppression systems that provide the same efficiency at reduced mass and/or volume.

Disclosure of Invention

The invention aims to meet all or part of this need and relates to an aircraft comprising a cockpit, at least one propulsion assembly and a fire extinguishing system dedicated to each propulsion assembly, each fire extinguishing system comprising two reservoirs, a control associated with each reservoir, each of said reservoirs containing a fire extinguishing agent, which can be actuated by a pilot to open each reservoir in order to release the fire extinguishing agent from the reservoir, and a detection assembly configured to detect a fire in the propulsion assembly dedicated to the fire extinguishing system and, if appropriate, to issue a fire warning signal intended for a visual or audible transducer located in the cockpit, characterized in that the propulsion assembly comprises a first compartment and a second compartment, each compartment comprising at least one fire zone, and in that, the fire suppression system includes a bypass valve controlled by a positioning unit, a set of conduits connecting each reservoir to each of the firing zones through the bypass valve, the positioning unit is configured to detect a fire in the one or more firing zones in the first compartment and, if appropriate, to control the bypass valve such that the bypass valve adopts a first state, referred to as a controlled state, otherwise the bypass valve is controlled to adopt a second state, referred to as a default state, in the first state, upon activation of the control associated with a reservoir, the fire suppressant in the reservoir is discharged towards the one or more fire zones in the first compartment, in the second state, the fire suppressant in the reservoir is discharged toward the fire zone of the second compartment after activation of the control associated with the reservoir.

According to the invention, the fire extinguishing system is capable of determining whether the first compartment is on fire in case of fire and, if the first compartment is on fire, of directing the diffusion of the fire extinguishing agent only towards one or more fire zones in the first compartment or otherwise towards one or more fire zones in the second compartment. Thus, the volume of fire suppressant in each reservoir may be reduced compared to the prior art, as it is no longer necessary to contain a volume that allows the fires in all of the fire zones of the propulsion assembly to be extinguished.

Drawings

The above-mentioned and other features of the present invention will become more apparent upon reading the following description of exemplary embodiments, which description is given with reference to the accompanying drawings, in which:

FIG. 1 is a schematic representation of a prior art fire suppression system, which has been described;

FIG. 2 is a schematic representation of an aircraft according to the present invention, the aircraft including a propulsion assembly and a fire suppression system dedicated to the propulsion assembly;

fig. 3 is a schematic representation of the fire suppression system of the aircraft shown in fig. 2, similar to fig. 1.

Detailed Description

Referring to fig. 2 and 3, the aircraft a has at least one propulsion assembly 10 attached below each wing W thereof. Each propulsion assembly 10 has a nacelle 11 enclosing an engine (not shown) and an engine fastening pylon 12 fastened under the wing W of the aircraft, and the engine is attached under the engine fastening pylon.

The propulsion assembly 10 is divided into a first compartment K1 and a second compartment K2. Each compartment K1, K2 comprises at least one ignition zone Z1, Z2. The fire zones Z1, Z2 of the propulsion assembly 10 are separated from each other by walls and fire seals (not shown) to contain any fire within the boundaries of one fire zone and prevent the fire from spreading to another.

It should be noted that in the example shown in fig. 3, two ignition zones Z1, Z2 are shown, wherein one ignition zone Z1 belongs to the first compartment K1 and one ignition zone Z2 belongs to the second compartment K2. In the remainder of the description, unless otherwise stated, this embodiment will be described in which each compartment K1, K2 comprises a single ignition zone Z1, Z2.

The aircraft a comprises a fire extinguishing system 20 dedicated to each propulsion assembly 10 for detecting any possible fire and extinguishing the fire via delivery of a fire extinguishing agent.

Conventionally, the fire extinguishing system 20 of the propulsion assembly 10 comprises two reservoirs R1, R2 (for example of the same capacity) each containing a volume of fire extinguishing agent, a set of pipes (lines shown in the figures) connecting the reservoirs R1, R2 to all the fire zones Z1, Z2, a detection assembly 21 for detecting a fire and, if appropriate, triggering a fire warning in the cockpit of the aircraft a, and two enabling controls C1, C2 located in the cockpit which can be actuated by the pilot to trigger the discharge of fire extinguishing agent towards the fire to be extinguished, in particular when a fire warning is issued and the pilot hears the fire alarm.

Each reservoir R1, R2, for example located in the boom 12 or in the fuselage 13 of the propulsion assembly 10, is equipped with an opening and triggering system.

For example, the opening and triggering system comprises discharge heads Rd1, Rd2 screwed onto the reservoir and a pyrotechnic cup (not shown) arranged in the discharge heads Rd1, Rd2 opposite a seal (not shown) near the reservoir. The pyrotechnic cartridge of the first reservoir R1 is ignited by actuation of the first activation control C1 to break the seal and release the pressurized fire suppressant from the first reservoir R1. Similarly, the pyrotechnic cartridge of the second reservoir R2 is ignited by actuation of the second activation control C2 to break the seal and release the pressurized fire suppressant from the second reservoir R2. For example, the first and second controls C1 and C2 are buttons or levers.

The detection assembly 21 includes a detection unit 22, for example, in the body 13, and a plurality of detection circuits L (only one detection circuit is shown in fig. 3) electrically connected to the detection unit 22. Each detection circuit L comprises at least one portion of a fire zone Z1, Z2 dedicated to the propulsion assembly 10, i.e. for each fire zone Z1, Z2 in each compartment K1, K2, there is at least one portion of a detection circuit L. A part of the detection circuit L comprises, for the fire zones Z1, Z2 to which it is dedicated, at least one fire sensor 23, 24 arranged in said fire zones Z1, Z2. In fig. 3, a single detection circuit L is shown comprising a portion with a fire sensor 23 dedicated to the fire zone Z2 in the second compartment K2 and a portion with a fire sensor 24 dedicated to the fire zone Z1 in the first compartment K1.

The detection unit 22 continuously measures the electrical value of the circuit formed by each detection loop L and issues a Fire alarm signal S _ Fire when the measurement result of the electrical value indicates a Fire. The Fire warning signal S _ Fire is received by at least one visual and/or audible transducer 25 located in the cockpit in order to trigger a Fire warning intended for the pilot and to warn them of a Fire in the propulsion assembly 10.

In the case where the measured electrical value is a resistance (in this case, an equivalent impedance measurement), the detection unit 22 issues a Fire alarm signal S _ Fire when the resistance value measured on at least one detection loop L falls within a range of predetermined values.

According to the invention, the fire extinguishing system 20 is able to determine whether a fire zone Z1, Z2 in a compartment K1, K2 is on fire in case of a fire and to direct the diffusion of the fire extinguishing agent only towards a compartment K1, K2 comprising a fire zone Z1, Z2 on fire or otherwise towards another compartment K1, K2.

To this end, the fire extinguishing system 20 according to the invention comprises:

a bypass valve 26 having an inlet 26a and two outlets 26b, 26 c. The inlet 26a of the bypass valve 26 is connected via a conduit to each reservoir R1, R2, whereas the first outlet 26b leads via a conduit into the fire zone Z1 in the first compartment K1 and the second outlet 26c leads via a conduit into the fire zone Z2 in the second compartment K2.

A positioning unit 27 to which both the one or more detection circuits L dedicated to the ignition zone Z1 in the first compartment K1, and the bypass valve 26 are electrically connected.

The bypass valve 26 is configured to be commanded to adopt two states, a first state, referred to as the controlled state, in which the fluid path extends through the valve from the inlet 26a to the first outlet 26b leading to the first compartment K1, and a second state, referred to as the default state, in which the fluid path passes through the valve from the inlet 26a to the second outlet 26c leading to the second compartment K2.

In one embodiment, the bypass valve 26 is for example of the electromechanical type and comprises a body (not shown) having an inlet to which the discharge head of each of the two reservoirs R1, R2 is fluidly connected, for example by means of a Y-shaped coupling, and two fluid outlets, one of which opens via a duct into the fire zone Z1 in the first compartment K1 and the other of which opens via another duct into the fire zone Z2 in the second compartment K2. The bypass valve 26 includes an actuator (not shown) electrically connected to the positioning unit 27 to allow movement of a movable door (not shown) in the body of the bypass valve 26. The movable gate may be located in one of two positions to orient the fire suppressant into the body of the bypass valve 26 via the fluid inlet 26 a: a first position corresponding to a controlled state of the bypass valve 26 and a second position corresponding to a default state of the bypass valve 26.

The positioning unit 27 is configured to measure the electrical value of the electrical circuit formed by one or more portions of the detection circuit L dedicated to the first compartment K1 and to send a control signal S _ Com to the bypass valve 26 to command said valve to adopt its controlled state if the measured value indicates a fire; otherwise the bypass valve 26 remains in its default state.

For example, the measured electrical value is a resistance (equivalent impedance measurement). In this case, the positioning unit 27 transmits the control signal S _ Com when the measured resistance value is within the range of the predetermined value.

If there is a fire in fire zone Z1 in first compartment K1, the detection logic implemented by fire suppression system 20 is as follows:

1) the positioning unit detects a fire in the firing zone Z1 and sends a control signal S _ Com to the bypass valve 26 in order to position the bypass valve in its controlled state. At the same time, the detection unit 22 detects a Fire in the propulsion assembly 10 and issues a warning signal S _ Fire. The warning signal S _ Fire is converted by a suitable transducer 25 located in the cockpit into a visual and/or audible alarm intended for the pilot.

2) The pilot then initiates the firing sequence and actuates the first control C1: the fire suppressant in the first reservoir R1 is released towards the first compartment K1 to extinguish a fire detected in the fire zone Z1.

3) In the event that a fire alarm in the cockpit is still active a few seconds after activation of the first control C1, the pilot actuates the second control C2 and the fire suppressant in the second reservoir R2 is released and discharged towards the first compartment K1.

If there is a fire in the fire zone in the second compartment K2, the detection logic implemented by the fire suppression system 20 is as follows:

1) the positioning unit 27 does not detect a fire in the first compartment K1; the bypass valve 26 remains in a default state. In contrast, the detection unit 22 detects a Fire in the propulsion assembly 10 and issues a signal warning signal S _ Fire. The warning signal S _ Fire is converted by a suitable transducer 25 located in the cockpit into a visual and/or audible alarm intended for the pilot.

2) The pilot then initiates the firing sequence and actuates the first control C1: the fire suppressant in the first reservoir R1 is released towards the second compartment K2.

3) In case the fire alarm is still active after a few seconds, the pilot actuates the second control C2 and the extinguishing agent in the second reservoir R2 is released and discharged towards the second compartment K2.

Preferably, the logic is designed such that once the bypass valve 26 has been positioned in its controlled state and either control C1 or control C2 has been actuated, only maintenance operations by the operator on the fire suppression system 20 can return the bypass valve 26 to its default state.

In case each compartment K1, K2 of the propulsion assembly 10 contains a single fire zone Z1, Z2, the amount of fire suppressant contained in each reservoir R1, R2 of the fire extinguishing system 20 according to the invention is limited by the amount necessary to extinguish the fire of the most important fire zone of Z1 and Z2.

Thus, the design of the fire extinguishing system according to the invention makes it possible to reduce the amount of fire extinguishing agent contained in each reservoir R1, R2 and thus the on-board mass of the aircraft a, compared to the prior art.

In the case of a propulsion assembly 10 having more than two ignition zones, for example if one or both compartments each comprise a plurality of ignition zones, the fire detection only system 20 is modified for such a case as described above as follows: if the first compartment includes multiple fire zones, the first fluid outlet 26b of the bypass valve 26 opens via a conduit into each of the first compartments K1, and if the second compartment includes multiple fire zones, the second fluid outlet 26c of the bypass valve 26 opens via a conduit into each of the second compartments K2.

Furthermore, in this case, the positioning unit 27 is also connected to the bypass valve 26, one or more portions of the detection circuit L dedicated to the ignition zone in the first compartment K1 (and therefore to the ignition sensor of the detection circuit). The positioning unit 27 measures the electrical value of the electrical circuit formed by said one or more parts and sends a control signal S _ Com to the bypass valve 26 to control said valve 26 so that it adopts its controlled state if the signal has a value indicating a fire in the first compartment K1.

In the latter case, the amount of fire suppressant contained in each reservoir R1, R2 of the fire suppression system 20 according to the invention is limited by the amount necessary to extinguish a fire of the most important compartment, i.e. the compartment in which the most fire suppressant is required to extinguish the fire based on fire simulation (e.g. taking into account a combustible liquid line through the compartment, a larger volume or more ventilation). Here again, the design of the fire extinguishing system 20 according to the invention thus makes it possible to reduce the amount of fire extinguishing agent contained in each reservoir R1, R2, and thus the onboard mass, compared to the prior art.

The controlled/default state of selecting which compartment between first compartment K1 and second compartment K2 to use for bypass valve 26 may be arbitrary. In another example, considering the architecture of the propulsion assembly (type of combustible fluid, number of pipes carrying the combustible fluid, environmental conditions such as close to the engine and its hot components), the choice is made so that the controlled state of the bypass valve delivers the extinguishing agent to that compartment K1, K2 which has the highest probability of fire risk compared to the other compartment K2, K1 to the one or more fire zones.