The invention regards a turbine generator system that comprises a gas turbine engine and an electrical generator coupled to the gas turbine engine, wherein the gas turbine engine is located in a compartment having a compartment wall. A ventilation system is provided that comprises: at least one air inlet arranged in the compartment wall and configured to allow air to flow into the compartment; at least one air outlet arranged in the compartment wall and configured to allow air to flow out of the compartment; at least one electric cooling fan with an adjustable fan speed located in, upstream or downstream of the air inlet, the electric cooling fan adjusting by its fan speed the amount of air flowing into the compartment; and temperature sensing means sensing the temperature inside the compartment or at the air outlet. The ventilation system is configured such that the cooling fan adjusts its fan speed depending on the temperature sensed by the temperature sensing means.

In accordance with at least one aspect of this disclosure, there is provided a system for an aircraft engine. In embodiments, the system includes an accessory box and a fuel accessory located in an interior space within the accessory box, where a vent is defined through a wall of the accessory box. In embodiments, the vent includes a plurality of holes or slots in an outer wall of the accessory box for passage of gaseous fuel from the interior space. In embodiments, the vent is configured for passive ventilation of the interior space.

In accordance with at least one aspect of this disclosure, there is provided a system for an aircraft engine. In embodiments, the system includes an accessory box and a fuel accessory located in an interior space within the accessory box, where a vent is defined through a wall of the accessory box. In embodiments, the vent includes a plurality of holes or slots in an outer wall of the accessory box for passage of gaseous fuel from the interior space. In embodiments, the vent is configured for passive ventilation of the interior space.

A propulsive assembly for aircraft comprising an engine, a nacelle arranged around the engine and a pylon supporting the engine, the nacelle including two engine cowls and reversing cowls, each cowl having an internal skin, characterized in that at least one of the cowls of the nacelle comprises at least one box arranged in a space situated between the internal skin of the cowl and the engine, the box delimiting a volume of inert material, the inert material being flame retardant foam. This box partially blocks a zone of the engine where a fire is likely to begin, which makes it possible to limit the volume of a fire zone of the engine, and thus reduce the quantity of extinguishing agent which is necessary to extinguish a fire in the zone of the engine concerned.

A gas turbine engine includes an engine core having a compressor, a combustor fluidly connected to the compressor, and a turbine fluidly connected to the combustor. A core nacelle is disposed radially outward of the engine core. A cavity is disposed between an inner surface of the core nacelle and an outer surface of the engine core. The cavity includes a vent disposed at an aft end. The vent includes at least one flap configured to be maintained in an unrestricted position and in a restricted position. An actuator is configured to control the position of the at least one flap.

A gas turbine engine includes an engine core having a compressor, a combustor fluidly connected to the compressor, and a turbine fluidly connected to the combustor. A core nacelle is disposed radially outward of the engine core. A cavity is disposed between an inner surface of the core nacelle and an outer surface of the engine core. The cavity includes a vent disposed at an aft end. The vent includes at least one flap configured to be maintained in an unrestricted position and in a restricted position. An actuator is configured to control the position of the at least one flap.

A labyrinth barrier is disclosed and comprises two or more members each defining respective vertical axes. One or more of the members are constructed at least in part of a shape memory material having a first energy state and a second energy state. The members are oriented relative to one another by their respective vertical axes in an original state to create a flow pathway that restricts fluid flow in a direction transverse to the respective vertical axes. The members are urged towards one another to further restrict the flow pathway when the shape memory material transitions from the first energy state to the second energy state.

An aircraft with at least one propulsion assembly and its fire-fighting system, which includes two reservoirs of extinguishing agent, and, associated with each reservoir, a control that can be actuated by a pilot to open the reservoir, a detection assembly to detect a fire and emit, if appropriate, a fire alert signal, the propulsion assembly including a first and a second compartment each including at least one fire zone, the fire-fighting system including a bypass valve controlled by a localization unit, a set of pipes connecting each reservoir to each of the fire zones through the bypass valve, the localization unit configured to detect a fire in a fire zone in the first compartment, and, if appropriate, control the bypass valve so it adopts a first state where the extinguishing agent in a reservoir is expelled towards the one or more fire zones in the first compartment after activation of the control associated with a reservoir, the bypass valve otherwise being controlled to adopt a second state, in which the extinguishing agent in a reservoir is expelled towards the one or more fire zones in the second compartment.

A propulsion assembly including a turbomachine attached to a pylon, and a fire-fighting system, the turbomachine including fire zones, the fire-fighting system including two reservoirs of pressurized extinguishing agent in the pylon and a distribution line connecting the reservoirs to nozzles. The distribution line includes connected pipes having a low point between the reservoirs and the nozzles, and, for each low point, a fluid drainage device for evacuating fluid. The drainage device includes a fluid passage for fluid evacuation from the distribution line and a mechanism for shutting off the fluid passage, the mechanism movable under effect of distribution line pressure, between a first position where it opens the fluid passage and a second position where it closes the fluid passage, the second position being reached when the pressure in the distribution line is greater than or equal to a predetermined pressure.

A ventilation device for controlling an air flow through at least one air inlet into an interior space of a gas turbine engine, comprises: at least one actuable closure device for the at least one air inlet, which has an open position for exposing the air inlet and can be transferred by actuation into a closed position for closing the air inlet; and a fire extinguishing device having an extinguishing agent arranged in a reservoir, wherein the fire extinguishing device is connected or can be connected to the interior space and the closure device in such a way that activation of the fire extinguishing device both leads to admission of extinguishing agent from the reservoir into the interior space and brings about actuation of the closure device to transfer the closure device into the closed position.