The invention relates to the construction of a woven cloth layer (3) designed in a way that it will be placed between metal sheets (2) in order to support them in the sealing element (1) which is mounted to provide sealing around the rotating elements like high/speed rotors, blades in the various mechanisms such as gas and steam turbines, aircraft engines

A seal device for a turbine is disposed around a rotor so as to separate a high-pressure space and a low-pressure space and includes: a plurality of thin plates arranged along an outer peripheral surface of the rotor. Each of the thin plates has a thin-plate tip surface facing the outer peripheral surface of the rotor; a first side plate disposed so as to face the high-pressure space and covering outer peripheral regions of first side surfaces; and a second side plate disposed so as to face the low-pressure space and covering outer peripheral regions of second side surfaces. The first side surface of each of the thin plates is covered with the first side plate in a region extending further to an inner side, in a radial direction of the rotor, than a region of the second side surface covered with the second side plate.

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 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.

A seal device for a turbine includes: a plurality of thin plates arranged along an outer peripheral surface of the rotor, each of the thin plates including a root portion disposed on an outer side in a radial direction of the rotor and supported on a stationary part of the turbine and a tip portion disposed on an inner side in the radial direction of the rotor and having a tip surface facing the outer peripheral surface of the rotor. Each of the thin plates is configured such that a width direction of the thin plate is parallel to an axial direction of the rotor at a side of the root portion, and the tip portion of each of the thin plates is configured such that an end on a side of the high-pressure space is positioned downstream of another end on a side of the low-pressure side.

A brush seal assembly includes a brush seal, a brush support portion, and an assembly support portion. The brush seal, which has a multitude of bristles forming an angle with respect to a radial direction of a rotating body rotated inside a casing, is disposed around an outer circumferential surface of the rotating body and is oriented with respect to the body's rotating direction. The brush support portion supports the brush seal by extending toward the rotating body while contacting a low-pressure side of the brush seal. The assembly support portion supports the brush seal and the brush support portion and to receive respectively a base end of the brush seal and an axial protrusion of the brush support portion. The brush support portion contacts the brush seal along a predetermined length, which is greater than that of a line following a bristle of the brush seal.

A shroud assembly for a turbine engine comprising a plurality of circumferentially arranged shroud segments having confronting end faces defining first and second radially spaced surfaces. The shroud assembly includes a forward edge spanning to an aft edge to define an axial direction and a set of confronting seal channels formed in each of the confronting end faces with a spline seal located within the confronting seal channels.

A fire seal structure prevents flame from coming out of a fire-prevention region of an aircraft. The fire seal structure includes: a plurality of walls including: a first wall provided on a first partitioning member; and a second wall provided on a second partitioning member. One of the plurality of walls is a spring wall that functions as a spring. The first and the second partitioning members define the fire-prevention region. The plurality of walls forms a labyrinth-shaped gap between the first and the second partitioning members. Each of the plurality of walls contains a refractory material and includes a front end part. When the first and the second partitioning members are stationary with respect to each other, the front end part is not in contact with another member, and the spring wall is disposed closest to a facing member, among the plurality of walls.

A seal assembly includes a seal nose, a bellows, and a plurality of bristles. The seal nose is configured to be in sealing contact with a rotating seal plate, the bellows extends between and couples the seal nose to a support structure, and the plurality of bristles extends from the support structure toward the bellows, with at least one bristle of the plurality of bristles being in contact with the bellows to damp vibration of the bellows.

A gas turbine engine includes a turbine section including at least one turbine rotor having at least one blade. A blade outer air seal is positioned radially outward of a radially outer tip of the at least one turbine blade. The blade outer air seal has a forward hook and an aft hook. The forward hook is supported on a forward retainer and the aft hook is supported on an aft hook retainer. The aft hook retainer provides structure to prevent rotation of the blade outer air seal relative to the aft hook retainer. There is an interference fit between the aft hook retainer and the forward retainer. A load path is provided from a static structure through the aft hook retainer to the forward retainer.