A fire resistance device is intended to be interposed between an upstream end of an aircraft turbine engine mounting structure and a cowling of the turbine engine delimiting an inter-flow compartment.

A fire resistance device is intended to be interposed between an upstream end of an aircraft turbine engine mounting structure and a cowling of the turbine engine delimiting an inter-flow compartment.

A seal for a wall of a vehicle includes a first plate that defines a first slot, and the first plate is to be coupled to the wall. The seal includes a second plate that defines a guide that extends outwardly from the second plate. The second plate is positioned adjacent to the first plate such that the guide is in communication with the first slot. The seal includes a third plate that defines a second slot that receives the guide, and the third plate is positioned adjacent to the second plate and is to be coupled to the wall.

A seal for a wall of a vehicle includes a first plate that defines a first slot, and the first plate is to be coupled to the wall. The seal includes a second plate that defines a guide that extends outwardly from the second plate. The second plate is positioned adjacent to the first plate such that the guide is in communication with the first slot. The seal includes a third plate that defines a second slot that receives the guide, and the third plate is positioned adjacent to the second plate and is to be coupled to the wall.

A method for manufacturing a metal component includes the following steps: a shell made of a titanium-based material is provided, the shell having a first surface and a second surface remote from the first surface; a covering layer made of a titanium fire-resistant material is produced by additive manufacturing on the shell such that the covering layer at least partially covers the first surface and/or the second surface; and, after the additive manufacturing step, the metal component is heat treated at a temperature of between 200° C. and 1000° C.

A seal arrangement configured to provide an airtight and fluid-tight seal between a first component and a second component, having a first pressure boundary seal disposable at least partially within the gap between the first component and the second component, the first pressure boundary seal being fixable to one of the first or second components to create an airtight seal with the other of the first or second component, the seal arrangement also having a first flame deflector that is configured to bridge across and cover the gap between the first component and the second component so as to create a fluid-tight seal over the gap between the first component and the second component, where the first flame deflector has a convex external shape so as to prevent any fluid impinging upon the first flame deflector from pooling on the first pressure boundary seal.

An aircraft includes an airframe defining a first enclosed space, an engine bay disposed within the first enclosed space, and a cooling system. The engine bay includes a firebox defining a second enclosed space and an engine disposed at least partially within the second enclosed space. The cooling system is configured to selectively fluidly couple the first enclosed space with the second enclosed space.

A fracturing system is disclosed. The fracturing may include a turbine engine; a fracturing fluid pump powered by the turbine engine via at least one reduction gearbox; an auxiliary mover for powering a hydraulic system for lubricating the turbine engine or the fracturing fluid pump or for powering a cooling system for cooling the turbine engine or the fracturing fluid pump; a first fire-control subsystem associated with the turbine engine; and a second fire-control subsystem associated with the auxiliary mover. The fracturing system is thus configured to provide fire-control and fire-fighting capabilities to minimize inadvertent consequences to the turbine engine as well as the auxiliary mover.

A maintenance system for a flame detector in an enclosure for an industrial machine, such as turbomachine, is disclosed. The maintenance system may include a conduit having an inlet at an exterior of the enclosure and an outlet at an interior of the enclosure. The outlet is adjacent the flame detector. The maintenance system also includes a source of air and a valve fluidly coupling the inlet of the conduit and the source of air. The valve is configured to deliver a compressed air from the source of air through the outlet of the conduit onto a surface of the flame detector, thereby removing contaminants from the surface and/or cooling the surface. A controller can be provided to automatically operate the cleaning and cooling system when a fault signal is observed.

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.