A sealing system including a first end and a second end with flexible bellows extending therebetween. The first end includes a base plate with an inner ring having an inner diameter. The inner ring is configured to receive a pipe therethrough. The pipe has an outer diameter, which is smaller than the inner diameter of the inner ring. The bellows of the sealing system has a first length in a first position and second length in a second position. Upon axial expansion of the pipe, the bellows is configured to move from the first position to the second position. The sealing system may also comprise a mechanical protective element, such as a shroud which extends around the bellows. Movement of the bellows can be further limited with rods extending from the shroud to a surrounding substrate or a cable fixing a maximum distance between the pipe and the shroud.

Expansion and movement joints are disclosed. An example apparatus includes a collar having a first aperture extending therethrough to receive a conduit, and a guide to receive the collar, where the guide has a second aperture that defines an inner surface of the guide, and where the inner surface of the guide is larger than an outer surface of the collar to define a gap therebetween.

A system is provided for a nacelle of an aircraft propulsion system. This system includes a tubular outer structure, a tubular inner structure and a seal assembly. The tubular inner structure projects through a bore of the tubular outer structure. The seal assembly is configured to close an end of an annulus between the tubular outer structure and the tubular inner structure. The seal assembly includes a seal land and a seal element. The seal land includes a seal land mount that circumscribes and is attached to the tubular inner structure. The seal land mount is configured with a v-shaped sectional geometry. The seal element is attached to the tubular outer structure. The seal element circumscribes and is sealingly engaged with the seal land. The seal element may be configured from or otherwise includes a polymer material.

An interface system for mechanically decoupling a cooling system includes: a housing having an opening; an inset having opposite first and second sides; an interface body having first and second ends and a bore-hole open to the first and second ends thereof. The inset has a recess in the second side to accommodate the interface body. The interface body is at least partially inserted into the inset, and the inset is at least partially inserted into the opening in the housing such that the first side of the inset is inside the housing. The first side of the inset has an opening open to the bore-hole of the interface body. One end of the bore-hole is configured to slidably receive an inlet of a cooling pipe, and the other end of the bore-hole is configured to be connected, in a fluid-tight manner, with an external coolant supply or coolant discharge.

An apparatus for sealing a hole or a shape in a surface may be disclosed. According to an exemplary embodiment, a soft material may be provided containing an interior hole, an exterior surface, a top lip, and an outer area. In an exemplary embodiment, a bottom lip may be further incorporated. In another exemplary embodiment, a rough surface may be imprinted onto the pipe seal apparatus. The rough surface may be imprinted into the interior portion of the body and the exterior portion of the body and the top lip, or both. An adhesive pipe sealant may be used along the rough surface. The rough surface may have a higher overall surface area for the adhesive to bond to, creating a stronger bond and preventing delamination.

A system is provided for a nacelle of an aircraft propulsion system. This system includes a tubular outer structure, a tubular inner structure and a seal assembly. The tubular inner structure projects through a bore of the tubular outer structure. The seal assembly is configured to close an end of an annulus between the tubular outer structure and the tubular inner structure. The seal assembly includes a seal land and a seal element. The seal land includes a seal land mount that circumscribes and is attached to the tubular inner structure. The seal land mount is configured with a v-shaped sectional geometry. The seal element is attached to the tubular outer structure. The seal element circumscribes and is sealingly engaged with the seal land. The seal element may be configured from or otherwise includes a polymer material.

A retention mechanism provided for use with a first line and a second line comprises a flexible convoluted web, a first conduit, and a second conduit. The first conduit defines a first passageway through the web, and is configured to receive the first line through the first passageway. The second conduit defines a second passageway through the web, and is configured to receive the second line through the second passageway. The first and second conduits are attached to and surrounded by the web such that the web enables movement of the first and second lines when the first and second lines are fixed respectively to the first and second conduits and extend respectively through the first and second passageways.

The present invention provides an arrangement for passing a line in a load-free manner through a pressure frame of a fuselage of an aircraft or spacecraft, including an opening penetrating the pressure frame, through which opening the line is passed, the line being mechanically decoupled from the pressure frame; and a flexible sealing device arranged outside the opening at least in portions, which sealing device is simultaneously operatively connected to the line and the pressure frame for the pressure-tight separation of a first side from a second side of the pressure frame. The present invention also provides a fuselage for an aircraft or spacecraft having an arrangement of this type and an aircraft or spacecraft having an arrangement of this type or having a fuselage of this type.

A seal assembly for a fluid transfer tube in a gas turbine engine is disclosed. In various embodiments, the seal assembly includes a base member having a first side configured to mate with a casing and a second side opposite the first side, an annular ring configured to mate with the second side of the base member and to surround a portion of the fluid transfer tube, a first O-ring disposed between the annular ring and the fluid transfer tube, a second O-ring disposed between the base member and the annular ring, and an attachment ring configured to secure the annular ring and the base member to the casing.

A method of manufacturing a composite connector for a fluid transfer conduit is provided which comprises applying continuous fibre reinforcement, oriented at least partially circumferentially and pre-impregnated with a thermoplastic polymer to a tubular mould portion which extends substantially parallel to a central axis C; applying at least one further mould portion to form a complete mould in which the continuous fibre reinforcement is enclosed and injecting a thermoplastic polymer into the mould to form a connector with a tubular hub portion and a flange portion which extends from the hub portion at an angle to the central axis C. The tubular hub portion comprises a tubular seal section with an inner layer and an outer wherein the inner layer comprises the continuous fibre reinforcement and the outer layer comprises the injected thermoplastic polymer.