A gas turbine engine includes first and second arc segments that each have leading and trailing sides and first and second circumferential sides. The first circumferential side includes a first slot portion and the second circumferential side includes a second slot portion. The first and second slot portions are in registration and together define a seal slot. At least the first slot portion has a first concave arced back wall. A feather seal is entrapped in the seal slot and includes first and second feather seal circumferential sides. At least the first feather seal circumferential side has a first convex arced edge that is adjacent the first concave arced back wall of the first slot portion.

A seal segment includes a retainer extending in a circumferential direction of a rotary shaft on an outer circumferential side of the rotary shaft; a first seal body which has a plurality of first thin plate seal pieces extending inward in a radial direction from the retainer and laminated in the circumferential direction; a high-pressure side plate; a low-pressure side plate; and a second seal body having a plurality of second thin plate seal pieces which are laminated at an end portion of the retainer in the circumferential direction, extend inward in the radial direction, and have fluttering resistance higher than the first thin plate seal piece. The high-pressure side plate and the low-pressure side plate cover at least a part of the second seal body in the circumferential direction.

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.

A sealing structure for a gas turbine includes a turbine rotor disk, a turbine blade coupled the turbine rotor disk, and an interstage disk interposed between adjacent turbine rotor disks. The turbine blade includes a blade circumferential surface protruding axially and extending in a circumferential direction of the turbine rotor disk and mutually engaging with a disk circumferential surface formed circumferentially on the turbine rotor disk. The interstage disk includes a rim portion and a groove formed in the rim portion. A plurality of static ring seals are mounted in the groove, each static ring seal facing toward the blade circumferential surface and the disk circumferential surface. The static ring are configured such that an outer circumferential surface of all the static ring seals contact the blade circumferential surface and the outer circumferential surface of at least one of the static ring seals does not contact the disk circumferential surface.

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.

Embodiments of the disclosure provide a seal strip for a seal assembly for a turbomachine. The seal strip includes a retaining portion for fixed coupling within a recess in a stationary component of the turbomachine. A plurality of leaf members extend from the retaining portion, and a slit extends between adjacent leaf members of the plurality of leaf members. Each leaf member includes a first stepped edge and an opposing, second stepped edge, and the first stepped edge and the second stepped edge of adjacent leaf members are configured to sealingly mesh in a mounted state of the seal strip in the turbomachine.

A nozzle segment for a gas turbine engine includes an arcuate outer vane platform segment. An arcuate inner vane platform segment spaced from the arcuate outer vane platform segment. A multiple of airfoils between the arcuate inner vane platform segment and the arcuate outer vane platform segment, the arcuate outer vane platform segment includes a scallop slot and a seal that seals the scallop slot.

The present disclosure is directed to a gas turbine engine including a turbine rotor assembly that includes a first turbine rotor and a second turbine rotor. The first turbine rotor includes an outer rotor and a plurality of outer rotors extended inwardly along a radial direction from the outer rotor. The second turbine rotor includes an inner rotor and a plurality of inner rotor airfoils extended outwardly along the radial direction from the inner rotor. The plurality of outer rotor airfoils and inner rotor airfoils are disposed in alternating arrangement along a longitudinal direction. One or more rotating seal interfaces are defined between the first turbine rotor and the second turbine rotor.

A steam turbine system includes: a steam turbine having a casing into which steam is fed from an outside of the casing and a rotating shaft that is provided within the casing so as to be rotatable around a central axis; a deaerator that is connected to the steam turbine and that deaerates leaked steam that has leaked from a gap between the casing and the rotating shaft to the outside of the casing; a vacuum pump that is connected to the deaerator and that lowers a pressure within the deaerator; and a shaft sealing device that is connected to the deaerator and that seals the gap between the casing and the rotating shaft. The shaft sealing device has a seal member having a seal body, a housing, a biasing member, and a negative-pressure introduction part.

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.