In some embodiments, apparatuses are provided herein useful to sealing a gap between a movable flap and a stationary structure, such as a gap between a gas turbine engine nozzle flap and a corresponding sidewall. An apparatus for sealing such a gap may be a dynamic skirted leaf seal which may include a flap arm and a wall arm opposite the flap arm. A distal end portion of the flap arm may comprise a first skirt and the distal end portion of the wall arm may comprise a second skirt that engages the first skirt. When positioned in a gap between the movable flap and the stationary structure, the skirted leaf seal may exert a force to urge the flap arm towards the flap and to urge the wall arm towards the structure to seal the gap.

In some embodiments, apparatuses are provided herein useful to sealing a gap between a movable flap and stationary structure, such as a gap between a gas turbine engine nozzle flap and sidewall. An apparatus for sealing such a gap may be a plunger seal which may include a plurality of plunger segments connected together using at least one flexure. When positioned in the gap, the flexures within the plunger segments pivot allowing rotation of each of the plurality of plunger segments about their respective pivot point, such that the plunger assembly seals and contours against the movable surface.

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.

Disclosed is an exhaust nozzle for a gas turbine engine, the exhaust nozzle comprising an outer frame extending along a longitudinal direction, a convergent petal pivotably attached to the frame and extending axially downstream and radially inward from the pivot, radially within the frame, and a sealing hinge arrangement between an upstream member and a downstream member of the exhaust nozzle. One of the upstream member or the downstream member defines a cylindrical socket having an opening along a cylinder axis which receives a corresponding cylindrical hinge element the other of the downstream member or upstream member, where the upstream member is defined by the frame and the downstream member is the convergent petal; or the exhaust nozzle further comprises a divergent petal downstream of the convergent petal and pivotably attached to the convergent petal, the upstream member being the convergent petal and the downstream member being the divergent petal.

A seal retainer for a fire seal of a gas turbine engine is provided. The seal retainer includes a core formed from a thermoplastic material and having a shape of a seal retainer with a top surface and a bottom surface, a first layer applied to the top surface of the core, and a second layer applied to the bottom surface of the core. The first layer and the second layer are formed from a high-temperature resistant material.

A seal segment includes a flapper seal, a wire mesh acting as a hinge for the flapper seal, and a spring. The flapper seal has a first surface and a second surface. The wire mesh includes a first section connected to the first surface of the flapper seal and a second section connected to the first section. The spring includes a first end that is in contact with the first section of the wire mesh to apply pressure to the first surface of the flapper seal and a second end adjacent the second section of the wire mesh.

Seals for gimbaling and/or fixed rocket engine nozzles, and associated systems and methods are disclosed. A representative rocket propulsion system includes a rocket engine having an exhaust nozzle, a seal plate carried by the exhaust nozzle, and a seal engaged with the seal plate. The seal includes at least one support, multiple pivotable first flaps, carried by the at least one support and positioned to contact the seal plate, and multiple pivotable second flaps, with an individual second flap positioned to shield a corresponding individual first flap. At least one forcing element is operatively coupled to at least one of the individual first flap or the individual second flap, to apply a pivoting force to the at least one of the individual first flap or the individual second flap.

A ceramic brush seal for a gas turbine engine, and a process for manufacturing the seal are provided. In one example, the process includes deinfiltrating an edge of a plurality of plies having a preimpregnated configuration. The edge is defined by a plurality of ceramic fibers extending away from a portion edge of a matrix infiltrated portion of each of the plies. In another example, the process includes masking an edge of a plurality of plies, the edge being defined by a plurality of ceramic fibers extending away from a portion edge of a body portion of each of the plies, and infiltrating the body portion of the plurality of plies with a ceramic matrix slurry. The plies are stacked, formed into a green body and then fired to form the component. The plies may include oxide/oxide woven ceramic fiber plies.

A thrust reverser of a nacelle is orientated at least in-part about a fan case of a turbofan engine. The thrust reverser includes an outer fixed structure assembly and a radial spacer. The outer fixed structure assembly circumferentially extends about a centerline and is spaced, at least in part, radially outward from the fan case. The radial spacer is engaged to the outer fixed structure assembly and is in sliding contact with the fan case.

A blocker door for a gas turbine engine thrust reverser having a tray with a base and sidewalls extending about the base to define a volume, the volume being closed by a cover that extends beyond the periphery of the tray. The extension of the cover beyond the periphery provides a sealing feature.