Fire retardant engine casing apparatus are disclosed. An example engine casing includes an inner shell circumferentially surrounding blades of a fan, a compressor, or a turbine, an outer shell positioned around the inner shell, and a fire retardant material between the inner shell and the outer shell.

A device for sealing a space at a juncture between elements of a nacelle, the device being non-flammable by heat, having a predetermined shape, and having a proximal end configured to be inserted into the space to be sealed so as to seal it, and a distal end configured to be fastened to an element of the nacelle at a fire area.

A hybrid electric powerplant can include an electric motor configured to convert electrical energy into kinetic energy to turn a propulsor, and a heat engine configured to convert a fuel into kinetic energy to turn the propulsor. The powerplant can include a firewall disposed around at least one of the electric motor or the heat engine to create an electric motor fire zone and a heat engine fire zone separate from the electric motor fire zone such that the electric motor is protected against a heat engine fire, and vice versa.

A hybrid electric powerplant can include an electric motor configured to convert electrical energy into kinetic energy to turn a propulsor, and a heat engine configured to convert a fuel into kinetic energy to turn the propulsor. The powerplant can include a firewall disposed around at least one of the electric motor or the heat engine to create an electric motor fire zone and a heat engine fire zone separate from the electric motor fire zone such that the electric motor is protected against a heat engine fire, and vice versa.

An assembly having an outer tubular portion delimiting an inner space, an inner tubular portion in the outer tubular portion, a fluid jacket in the inner tubular portion, a plurality of groups of at least four thermal flow sensors. For each group, the sensors of the group are disposed in the inner space and overall in one and the same plane perpendicular to a central line. In each group, the sensors of the group are distributed angularly about the central line. A control unit which, for each group, receives the data from each sensor of the group and which, on the basis of these data, determines a warning level. With such an arrangement, the monitoring of the values of the different thermal flow sensors makes it possible to monitor a potential problem at the fluid jacket.

An assembly having an outer tubular portion delimiting an inner space, an inner tubular portion in the outer tubular portion, a fluid jacket in the inner tubular portion, a plurality of groups of at least four thermal flow sensors. For each group, the sensors of the group are disposed in the inner space and overall in one and the same plane perpendicular to a central line. In each group, the sensors of the group are distributed angularly about the central line. A control unit which, for each group, receives the data from each sensor of the group and which, on the basis of these data, determines a warning level. With such an arrangement, the monitoring of the values of the different thermal flow sensors makes it possible to monitor a potential problem at the fluid jacket.

A fracturing device, a firefighting method thereof, and a computer readable storage medium are disclosed. The fracturing device includes a power unit, the power unit includes a muffling compartment, a turbine engine, and a firefighting system; the firefighting system includes a firefighting material generator, at least one firefighting sprayer and at least one firefighting detector, the at least one firefighting sprayer and the at least one firefighting detector are located in the muffling compartment, each of the at least one firefighting sprayer is connected with the firefighting material generator and configured to spray out firefighting material generated by the firefighting material generator.

An aircraft propulsion unit is described. The unit may include a gas generator with a fan surrounded by a casing. A nacelle may extend around the casing and define an annular compartment with the casing wherein some equipment may be housed. An air inlet may be configured so a ventilation air flow penetrates inside the compartment. An air outlet may be configured so a ventilation air flow is evacuated from the compartment. The propulsion unit may also include an air flow adjustment regulator. The air flow adjustment regulator may be configured to maintain a nominal value of the ventilation air flow circulating through at least one of the air inlet and of the air outlet under nominal operating conditions, and to reduce the value of this ventilation air flow when a fire is detected inside the compartment.

Methods and fire sealing systems for a panel of a gas turbine engine are provided. The fire sealing systems include a thermal blanket mounted on the panel, the thermal blanket having a close-out and defining a seal landing at a periphery edge of the panel, a seal retainer mounted to the panel along the seal landing, and a fire seal securely retained within the seal retainer, wherein at least one of the seal retainer or the fire seal comprises an extension portion and a blanket engaging portion such that a close-out volume formed between the thermal blanket and the fire seal above the close-out of the thermal blanket is enclosed.

Methods and fire sealing systems for a panel of a gas turbine engine are provided. The fire sealing systems include a thermal blanket mounted on the panel, the thermal blanket having a close-out and defining a seal landing at a periphery edge of the panel, a seal retainer mounted to the panel along the seal landing, and a fire seal securely retained within the seal retainer, wherein at least one of the seal retainer or the fire seal comprises an extension portion and a blanket engaging portion such that a close-out volume formed between the thermal blanket and the fire seal above the close-out of the thermal blanket is enclosed.