Aircraft propulsion assembly having a ventilation system and a fire-fighting system
A propulsion assembly with an outer compartment, an inner compartment, a supply pipe and a transfer pipe between the two compartments, a suction system between the two pipes, a regulating element that regulates the flow rate of air in the suction system and a fire-fighting system having a reservoir of extinguishing fluid, a discharge pipe connected to the reservoir, and a control system between the reservoir and the discharge pipe. The discharge pipe is configured and arranged to supply the transfer pipe when the control system is in the open position. The outside air is then driven by the suction system and passes through the two compartments in a forced manner and the extinguishing fluid reaches the transfer pipe to flow into the inner compartment.
1. A propulsion assembly for an aircraft, said propulsion assembly having:
a primary duct and a secondary duct,
an outer fairing having an external annular wall and an internal annular wall that delimit between them an outer compartment, wherein the external annular wall has an inlet opening,
an inner fairing having an external annular wall and an internal annular wall that delimit between them an inner compartment, wherein the external annular wall has at least one air exhaust aperture,
wherein the secondary duct is delimited between the internal annular wall of the outer fairing and the external annular wall of the inner fairing,
wherein the primary duct is delimited inside the internal annular wall of the inner fairing,
a suction system having an inlet, an outlet and mobile elements that are configured to draw air in via the inlet and deliver drawn-in air via the outlet,
a drive means configured to drive the mobile elements,
a transfer pipe fluidically connected to the outlet of the suction system,
a distribution pipe disposed in the inner compartment, fluidically connected to the transfer pipe and having a plurality of nozzles,
a supply pipe, of which one end opens into the outer compartment, and of which another end is fluidically connected to the inlet of the suction system,
a regulating means configured and arranged to regulate a flow rate of air in the suction system, and
a fire-fighting system having a reservoir containing an extinguishing fluid, a discharge pipe, of which a first end is fluidically connected to the reservoir, and a control system interposed between the reservoir and the discharge pipe that alternately adopts a closed position preventing the extinguishing fluid from flowing into the discharge pipe or an open position allowing the extinguishing fluid to flow into the discharge pipe, and
wherein a second end of the discharge pipe opens directly into the transfer pipe so as to supply the discharge pipe, when the control system is in the open position.
2. A propulsion assembly for an aircraft, said propulsion assembly having:
a primary duct and a secondary duct,
an outer fairing having an external annular wall and an internal annular wall that delimit between them an outer compartment, wherein the external annular wall has an inlet opening,
an inner fairing having an external annular wall and an internal annular wall that delimit between them an inner compartment, wherein the external annular wall has at least one air exhaust aperture,
wherein the secondary duct is delimited between the internal annular wall of the outer fairing and the external annular wall of the inner fairing,
wherein the primary duct is delimited inside the internal annular wall of the inner fairing,
a suction system having an inlet, an outlet and mobile elements that are configured to draw air in via the inlet and deliver drawn-in air via the outlet,
a drive means configured to drive the mobile elements,
a transfer pipe fluidically connected to the outlet of the suction system,
a distribution pipe disposed in the inner compartment, fluidically connected to the transfer pipe and having a plurality of nozzles,
a supply pipe, of which one end opens into the outer compartment, and of which another end is fluidically connected to the inlet of the suction system,
a regulating means configured and arranged to regulate a flow rate of air in the suction system, and
a fire-fighting system having a reservoir containing an extinguishing fluid, a discharge pipe, of which a first end is fluidically connected to the reservoir, and a control system interposed between the reservoir and the discharge pipe that alternately adopts a closed position preventing the extinguishing fluid from flowing into the discharge pipe or an open position allowing the extinguishing fluid to flow into the discharge pipe, and
wherein a second end of the discharge pipe opens directly into the outer compartment to supply the transfer pipe, when the control system is in the open position.
3. The propulsion assembly according to claim 1 , wherein the fire-fighting system also has a discharge sub-pipe, of which a first end opens into the discharge pipe, and of which a second end opens into the outer compartment.
4. The propulsion assembly according to claim 3 ,
wherein the control system has a first control sub-system and a second control sub-system,
wherein the first control sub-system controls the flow of the extinguishing fluid into the discharge pipe, and
wherein the second control sub-system controls the flow of the extinguishing fluid into the discharge sub-pipe.
5. An aircraft having at least one propulsion assembly according to claim 1 .
6. An aircraft having at least one propulsion assembly according to claim 2 .