A system has a surface intended to separate two chambers within the system. The surface has an aperture for allowing passage of at least one communication conduit. A shroud is positioned on the surface at the aperture, and has at least two portions defining a central opening to allow the communication conduit to pass through the aperture and shroud. The two portions of shroud have mating clamp ears in contact with each other. Securement members tighten the clamp ears against each other to provide a seal at an end of the shroud remote from the surface.

A retaining bracket is attached to a fuel nozzle for cooperating with a flange on a fuel transfer tube to prevent the fuel transfer tube from becoming disconnected from the fuel nozzle during engine operation. The retaining bracket is shaped so as to form an enclosure over a head of the nozzle, the enclosure acting as a fire shield to allow the nozzle to perform its intended functions for a predetermined period of time when exposed to an engine fire event.

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.

The invention relates to a seal for an aircraft incorporating a fire-resistant structure, and an aircraft incorporating at least one such a seal between structural elements of the aircraft connected to each other at a zone of the latter which may be a fire zone according to the standard ISO 2685:1998 or AC 20-135.

According to the invention, this seal (10) comprises: a seal body (11) at least partially elastomeric, the seal body defining at least one generally tubular or annular cavity (10A), and a fire-resistant structure (12) distinct from the seal body and disposed inside the cavity, the fire-resistant structure comprising an intumescent mass able to fill the cavity (10A) in an expanded state,
the intumescent mass being made of a rubber composition having an intumescence trigger temperature equal to or higher than 270° C., measured by a plane-plane rotary rheometer with a temperature scan from 23 to 380° C. according to a ramp of 10° C./min.

An aircraft firewall feedthrough device for accommodating a feedthrough member extending through an aperture of a firewall of an aircraft is provided. The device includes a plate configured to be attached to the firewall, a first tubular portion extending from a first side of the plate, a second tubular portion extending from a second side of the plate, and a grommet. The plate includes a feedthrough aperture. The first tubular portion, the second tubular portion and the feedthrough aperture cooperatively define a through passage for accommodating the feedthrough member. The grommet is retained inside the through passage. The grommet includes a hole for accommodating the feedthrough member through the grommet.

An aircraft firewall feedthrough device for accommodating a feedthrough member extending through an aperture of a firewall of an aircraft is provided. The device includes a plate configured to be attached to the firewall, a first tubular portion extending from a first side of the plate, a second tubular portion extending from a second side of the plate, and a grommet. The plate includes a feedthrough aperture. The first tubular portion, the second tubular portion and the feedthrough aperture cooperatively define a through passage for accommodating the feedthrough member. The grommet is retained inside the through passage. The grommet includes a hole for accommodating the feedthrough member through the grommet.

An electromechanical component arrangement for a gas turbine engine includes a mechanical component located at a first side of a firewall of a gas turbine engine and an electronic module of the electromechanical component connected to the mechanical component by a module cable. The electronic module is inserted through a module opening in the firewall from the first side to a second side, the second side having a lower operating temperature than the first side. A cover plate is installed over the module opening after the electronic module is inserted therethrough.

An electromechanical component arrangement for a gas turbine engine includes a mechanical component located at a first side of a firewall of a gas turbine engine and an electronic module of the electromechanical component in communication with the mechanical component separated from the mechanical component by a firewall, the firewall comprising a first side and a second side, the second side having a lower operating temperature than the first side. A vibration isolation structure is located at the second side. The electronic module is connected thereto and includes at least one vibration isolator secured to the firewall to vibrationally isolate the electronic module from gas turbine engine vibrations.

An electromechanical component arrangement for a gas turbine engine includes a mechanical component located at a first side of a firewall. An electronic module assembly of the electromechanical component is connected to the mechanical component and includes a housing, a mounting frame located in the housing and an electronic module secured to the mounting frame. The electronic module is operably connected to the mechanical component via a module cable. A vibration isolator is located in the housing to locate and support the mounting frame therein. The vibration isolator is configured to vibrationally isolate the electronic module from gas turbine engine vibrations. A cover plate is secured to the housing and the first side of the firewall, while the housing extends from the cover plate through a module opening in the firewall to a second side of the firewall having a lower operating temperature than the first side.

An electromechanical system for a gas turbine engine includes a mechanical component located at a first side of a firewall of a gas turbine engine, and an electrical motor located at a second side of the firewall and configured to drive the mechanical component. The electrical motor mechanically connected to the mechanical component through a firewall opening in the firewall, the first side having a higher operating temperature than the second side. An electrical connection extends between the mechanical component and the electrical motor via the same firewall opening.