A vane segment includes a blade ring, a plurality of vanes, and a caulking member. The blade ring includes a blade ring groove and a storage space forming portion. The blade ring groove includes a convex portion projecting from a second groove side surface of the blade ring groove to the first side. The storage space forming portion, in combination with an outer shroud, forms a storage space into which the caulking member enters. The caulking member is accommodated within the storage space, contacts with the blade ring groove and the outer shroud, and is exposed from an inner opening of the storage space.

A magnetic fire seal for a nacelle may comprise an exterior surface configured to form a sealing interface and an interior surface opposite the exterior surface. A fire-resistant material may be disposed between the exterior surface and the interior surface. A magnet may be located at the interior surface proximate the sealing interface. A portion of the fire-resistant material may be located between the magnet and the exterior surface.

An assembly is provided for rotational equipment. This assembly includes a stationary structure, a rotating structure rotatable about an axial centerline, and a non-contact seal assembly. The non-contact seal assembly is configured to substantially seal a gap between the stationary structure and the rotating structure. The non-contact seal assembly includes a seal shoe configured to sealingly engage the rotating structure axially along the axial centerline.

Seal ring groups to be assembled with edges of through holes of a gasket includes a plurality of sealing groups. One of the plurality of sealing groups has an inner peripheral shape different from an inner peripheral shape of another of the plurality of sealing groups to distinguish one sealing group from another sealing group.

A seal includes a ceramic matrix composite ply having woven ceramic-based fibers in a ceramic-based matrix. The ceramic matrix composite ply has at least one bend formed about a bend axis and defines at least one rounded portion. A sealed assembly and a method of making a seal are also disclosed.

A sealing assembly and a turbomachine including the sealing assembly are provided. The sealing assembly includes a sealing body configured to be inserted into an insertion hole of a second component adjacent to a first component, and a sealing protrusion, formed on one circumferential side of the sealing body, protruding toward one circumferential direction from the sealing body and configured to be inserted into a sealing groove formed on the other circumferential side of a sealing body of the first adjacent sealing assembly, the sealing body of the first adjacent sealing assembly being adjacent to the sealing body in a circumferential direction.

Systems and methods for delivering a buffer fluid to a shaft seal of a gas turbine engine are provided. An exemplary system includes, a buffer fluid source, one or more first conduits providing fluid communication between the buffer fluid source and the shaft seal along a first route, and one or more second conduits providing fluid communication between the buffer fluid source and the shaft seal along a second route different from the first route. A heat exchanger is also disposed along the first route to facilitate heat transfer between buffer fluid in the one or more first conduits and a cooling fluid.

Methods, apparatus, systems and articles of manufacture are disclosed. An inner shroud damper for a gas turbine engine includes: at least one carrier including a joint to couple to an inner shroud, the at least one carrier having a first side and a second side, and at least one mass damper coupled to the at least one carrier.

A seal segment comprises: a seal body having a plurality of thin-plate seal pieces that extend while being inclined forward in a rotational direction of a rotating shaft as the pieces draw farther inward in a radial direction of the rotating shaft, and that are layered in a circumferential direction of the rotating shaft; a pair of side plates extending in the circumferential direction so as to cover the seal body from both sides with respect to an axial direction of the rotating shaft; and a housing having a housing main body that accommodates the seal body while allowing the seal body to protrude inward in the radial direction, and an extending part that is provided to an end portion of the housing main body in the circumferential direction, and that extends inward in the radial direction along an end surface of the seal body in the circumferential direction.

A gas turbine engine includes a blade outer air seal, a ceramic vane, and a cooling passage circuit that extends through a first internal passage in the blade outer air seal and a second internal passage in the ceramic vane.