Provided is a combustor of a gas turbine including a combustion liner where combustion occurs, a transition piece connected to the combustion liner to allow combustion gases to pass through, and a honeycomb seal ring disposed between the combustion liner and the transition piece to prevent compressed air from leaking through a gap between the combustion liner and the transition piece. The honeycomb seal ring is inserted into the exit portion of the combustion liner to prevent compressed air from leaking when the combustion liner and the transition piece are coupled with each other.

The segmented seal carrier of a guide vane ring of a turbomachine has a number of segments that form two half-rings of the seal carrier when assembled. They are clamped together by their opposite-lying, corresponding lateral contact regions.

A sealing device includes a sealing main body surrounding a rotor shaft rotating about an axis from an outer periphery side. The sealing main body includes an inside surface facing an outside surface of the rotor shaft with clearance and a plurality of hole parts formed recessed to an outer side in a radial direction from the inside surface and arrayed in a circumferential direction of the inside surface and in a direction of the axis. The hole parts have an inner peripheral wall in which a spiral groove extending twisting toward the outer side in a radial direction is formed.

A sealing element for a turbomachine, in particular an aircraft engine, with a housing for the at least one rotating structural component is provided. The sealing element comprises a honeycomb structure for arrangement inside the housing, wherein the honeycomb structure extends in a first direction, wherein support structures are connected to the honeycomb structure in one piece and/or in a pattern-like manner and extend at least partially into the honeycomb structure, and the support structures extend at least partially or completely in a second direction that is different from the first direction. The support structures have planar portions, which are formed by at least one partially or completely closed cell together with the honeycomb structure.

A rotating labyrinth seal especially useful for effecting sealing between two plenums in aircraft gas turbine engines comprising a base and a plurality of radially-directed seal teeth rings extending circumferentially around the outer peripheral surface of the base. The fins in the rotating seal each having a discontinuity that reduces hoop stress on the outer radial surface. The discontinuities in each fin are offset from the discontinuities in the adjacent fins.

An inter-stage seal assembly includes annular seal land mounted inwardly of and to seal support ring and pre-swirlers in purge duct extending through land. Purge duct may be bounded by spaced apart duct walls and pre-swirlers include turning vanes in outer exhaust section. Purge duct may include plurality of enclosed purge passages circumferentially disposed around engine centerline and pre-swirlers include curved section in passages. Seal land may be bifurcated having forward and aft seal land sections and purge duct may include purge duct inlet located therebetween. Seal support ring may include flange attached to or integrally and monolithically formed with inner platform attached to nozzle vanes extending across turbine flowpath and exhaust section may be flush with platform. Labyrinth seal teeth mounted to turbine rotor may engage land, purge duct may extend between annular inlets and outlets, inlet may be between adjacent couple of seal teeth.

A circumferential seal for a rotating component comprising a static seal part and a rotating seal part having a common rotational axis. The rotating seal part comprises a fin seal, wherein the fin seal comprises a protective coating. A first portion of the fin seal has a first sealing gap to the static seal part and a second portion of the fin seal has a second sealing gap to the static seal part. The first sealing gap has a greater radial dimension than the second sealing gap.

The present disclosure generally relates to variable cellular structures, methods of making such cellular structures, and variable cellular flow discouragers for turbine engines for jet aircraft.

The invention relates to a sealing assembly for a fluid kinetic machine, in particular for an aircraft engine, for sealing a radial gap between a rotor and a stator, including at least one sealing support for retaining and/or fixing at least one sealing element, wherein the sealing support includes a first and a second radial web extending in a radial extension direction as well as an axial web extending in an axial extension direction, firmly bonded to the radial webs, and the radial webs form a receptacle for receiving an element of the stator. Therein, the radial webs are formed as sheet elements formed elongated in radial direction, wherein a radially interior end of the radial webs is respectively firmly bonded, in particular welded, to a radially exterior surface of the axial web.

An air seal in a gas turbine engine comprising a substrate. A bond coating layer is adhered to the substrate. An abradable layer is adhered to the bond coating layer. The abradable layer comprises a metal matrix discontinuously filled with a soft ceramic material.