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.

Disclosed are laminates comprising a carbon fiber reinforced polymer sheet and a layer of polysilazane and methods for producing such laminates.

Disclosed are laminates comprising a carbon fiber reinforced polymer sheet and a layer of polysilazane and methods for producing such laminates.

The invention relates to a method for producing a grid made of composite material for straightening an air flow for an aircraft turbine engine. The described method is based on the use of longitudinal members (301) which have recesses (303) to allow the penetration of connecting elements (304) into said recesses during the manufacture of the grid.

The invention relates to a method for producing a grid made of composite material for straightening an air flow for an aircraft turbine engine. The described method is based on the use of longitudinal members (301) which have recesses (303) to allow the penetration of connecting elements (304) into said recesses during the manufacture of the grid.

A thrust reverser cascade for an aircraft nacelle includes a plurality of blades having a first and a second surface, the blades being connected to members connected to attachment flanges for attaching the thrust reverser cascade to the nacelle. At least one of the surfaces of the blades is covered with at least one layer of fibers, each layer including a plurality of fiber pieces which are pre-impregnated with resin. The fiber pieces are superimposed on one another, positioned parallel to the aerodynamic surface of the blade and oriented in different directions.

A thrust reverser cascade for an aircraft nacelle includes a plurality of blades having a first and a second surface, the blades being connected to members connected to attachment flanges for attaching the thrust reverser cascade to the nacelle. At least one of the surfaces of the blades is covered with at least one layer of fibers, each layer including a plurality of fiber pieces which are pre-impregnated with resin. The fiber pieces are superimposed on one another, positioned parallel to the aerodynamic surface of the blade and oriented in different directions.

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.

A system of conjoined gas turbine engines has a first engine with a first propulsor having a first axis and a first engine core having a second axis, and a second engine with a second propulsor having a third axis and a second engine core having a fourth axis. The first axis and third axis are parallel to one another; and the second axis and fourth axis are angled from one another.