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.

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.

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 turbojet engine with two thrust reverser modules. Each module includes an outer casing, an inner casing and a securing system for securing the inner casing to the outer casing which comprises first and second hoods. A housing between the hoods has a securing wall, a seal with a sausage secured to the securing wall, and a crusher rigidly secured to the second hood and arranged so as to crush the sausage towards the securing wall when the second hood goes from the spaced-apart position to the close-together position. Therefore, the sausage moves in the longitudinal direction, thus limiting shearing of the seal and transverse movements owing to the manufacturing and assembly tolerances and the movements in flight.

Resonating patch for acoustic treatment comprising a resonant plate, a transducer and an electrical circuit electrically connected to the transducer, the resonant plate comprising a peripheral strip extending along the perimeter of the resonant plate.

The patch comprises cutouts together defining deformable lamellae having at least one end connected to the peripheral strip.

Guide systems for installing aircraft structures are disclosed. An example apparatus includes a first guide system structured to removably couple to a first aircraft structure having a first hinge component. A second guide system is structured to removably couple to a second aircraft structure having a second hinge component. The first guide system is to engage the second guide system to enable alignment between the first hinge component and the second hinge component during assembly of the first aircraft structure and the second aircraft structure.

The present disclosure provides a method for manufacturing a preform made of reinforcement fibers woven in a longitudinal direction. The preform is impregnated with resin in order to form an elongated element having a variable transverse cross-section. In one form, the method includes the step of simultaneously including a reduction (or increase) in width and an increase (or reduction) in height. The variable cross-section includes, along the length thereof, a consistent number (c) of continuous warp threads arranged in layers. The method for reducing width includes carrying out a change in weave, adding additional weft threads, and simultaneously drawing the teeth of the longitudinal beater reed closer together so as to increase the number of layers.

A thrust reverser track beam may comprise a noise suppressing structure. The noise suppressing structure may form the airflow surface of the track beam. The noise suppressing structure may be riveted, bolted, or bonded to the track beam.

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.

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.