A rotor assembly of a gas-turbine engine may comprise a first rotor blade, a second rotor blade, a third rotor blade, a first platform sealing assembly and a second platform sealing assembly. The first platform sealing assembly may be disposed between a first platform of the first rotor blade and a second platform of the second rotor blade. The second platform sealing assembly may be disposed between the second platform and a third platform of the third rotor blade.

A hydrostatic advanced low leakage seal configured to be disposed between relatively rotatable components. The seal includes a base. The seal also includes a shoe extending circumferentially. The seal further includes a first beam operatively coupling the shoe to the base, the first beam having a first thickness. The seal yet further includes a second beam operatively coupling the shoe to the base, the second beam having at least a portion thereof with a second thickness that is less than the first thickness.

An assembly includes first and second core gaspath walls. Each of the core gaspath walls defines a core gas path side and a non-core gas path side. The first and second core gaspath walls are arranged next to each other and define a gap therebetween. There is a seal arranged on the non-core gas path side that bridges over the gap to seal the gap. A spring device has a plurality of spring elements. The spring elements bias the seal against the non-core gas path sides of the first and second core gaspath walls.

A seal segment (11) includes a retainer (21), a seal body (13) having a thin plate seal piece (20), a high-pressure side plate (23), a low-pressure side plate, a retainer simulating section (51) further extending in the circumferential direction (Dc) from an end portion of the retainer (21) in the circumferential direction (Dc), and a block body (50) including a seal body simulation section (53) extending inward in the radial direction (Dr) from the retainer simulation section. The high-pressure side plate (23) and the low-pressure side plate cover at least a part of the seal body simulation section (53) of the block body (50).

A shroud attaching structure of a gas turbine includes: a support provided around an axis of the gas turbine and inside a casing of the gas turbine in a radial direction; and a shroud assembly attached to the support so as to cover an inner peripheral surface of the support, the shroud assembly being formed by laminating a large number of plate-shaped shroud elements containing a ceramic matrix composite. The shroud elements are lined up in a circumferential direction of the support. The adjacent shroud elements are arranged so as to be slidable on each other.

Turbomachine modules, for example for an aircraft, include a turbine nozzle having several sectors (S), each sector having guide vanes extending between inner and outer platform elements, at least one of the platform elements of each sector carrying, on the one hand, at least one sealing blade configured to ensure fluid sealing between the platform element and the adjacent structural element, and, on the other hand, a device configured to hold the at least one sealing blade in a sealing position. The device includes a leaf spring having a middle portion fixed to the platform element, and opposite end portions which are supported on the sealing blade carried by the platform element.

A seal segment for a turbine and an assembly for sealing the gaps between seal segments and stator vanes of a turbine. The seal segments have a plate-shaped wall, the first lateral surface of which faces the vane tips in the assembled state of the seal segments, is surrounded by a closed circumferential edge, and can be divided into four lateral wall sections, and the plate-shaped wall has a seal element which is arranged over the entire surface of the lateral surface. A number of seal lamellae which are secured on one side are provided on at least one of the lateral wall sections and/or on at least one of the seal lateral wall sections facing adjacent seal segments when the seal segments are assembled in a turbine so as to form a ring in order to reduce a flow along the corresponding lateral wall section.

A compressor seal-ring assembly includes a seal formed of a nickel, cobalt or iron-based superalloy; a counterface positioned for sealing interaction with the seal; and a lubricant coating on the seal, the lubricant coating being formed of a CoCrAlY-containing material.

A rotor assembly of a gas-turbine engine may comprise a first rotor blade, a second rotor blade, a third rotor blade, a first platform sealing assembly and a second platform sealing assembly. The first platform sealing assembly may be disposed between a first platform of the first rotor blade and a second platform of the second rotor blade. The second platform sealing assembly may be disposed between the second platform and a third platform of the third rotor blade.

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.