A seal device has a seal main body. The seal main body includes a plurality of holes arranged to be recessed from a facing surface facing a rotor which rotates around an axis, and an ejection flow path which guides a fluid to bottom portions of the holes and ejects the fluid from the bottom portions.

A method of applying a braze component to a honeycomb structure may comprise: applying at least a partial vacuum within a chamber, the chamber defined at least partially by a vacuum device and a cover, the honeycomb structure disposed within the chamber, the braze component disposed between the honeycomb structure and the cover; pulling the cover towards the braze component in response to applying the partial vacuum; and pulling the braze component into a plurality of hexagonal cells defined by the honeycomb structure in response to pulling the cover towards the braze component.

The present invention relates to a labyrinth seal for a turbine engine, in particular of an aircraft, comprising a rotor element and a stator element extending around the rotor element, the rotor element being suitable for rotating relative to the stator element about an axis of rotation having an axial direction (DA), the rotor element comprising an annular lip having an outer radial end extending towards an abradable element (57) carried by the stator element, the outer radial end of the annular lip having a corrugation in the axial direction (DA) and a non-zero axial expanse (E.sub.5) associated with the corrugation, the abradable element (57) comprising a plurality of cells (50a, 50b) arranged adjacent to one another along the axial direction (DA) and an ortho-radial direction (O), the cells (50a, 50b) comprising walls which extend in an essentially radial direction, the cells being distributed with a first cell density in a first densified annular zone (Z.sub.51) of the abradable element, said densified annular zone (Z.sub.51) being located opposite the radial end of the lip, said densified annular zone having an axial expanse less than or equal to the axial expanse of the outer radial end of the lip, the cells being distributed according to a reference density of cells outside said first zone, the first density being greater than the reference density.

A sealing device seals a gap between an outer circumferential surface of a rotor and an inner circumferential surface of a stator. The sealing device includes a sealing ring provided on the stator and having a free-cutting material, in which a convex portion and a concave portion are alternately formed in an axial direction, on a surface facing the rotor; a plurality of radial fins protruding radially outward from the outer circumferential surface of the rotor; and oblique fins which obliquely protrude from the outer circumferential surface of the rotor toward both ends of the free-cutting material of the sealing ring in the axial direction from the outside of the both ends.

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.

An abradable member for a turbomachine turbine, including a cellular structure including walls defining wells which open through a wear face. The cellular structure includes at least one flow straightener jutting from the wear face.

The invention relates to an assembly for a turbomachine, comprising a stator (1) and a rotor (2) rotatable relative to the stator (1) about an axis, the rotor (2) comprising blades each comprising a vane (3) connected to a radially inner platform (5), a block of abradable material (6) extending radially inwardly from the radially inner platform (5) the stator (1) having a shroud comprising an annular area (9), at least one lug (12) extending radially outwardly from said annular area (9), the radially outer end of the lug (12) cooperating with the block of abradable material (6).

A sealing device seals a gap between an outer circumferential surface of a rotor and an inner circumferential surface of a stator. The sealing device includes a sealing ring provided on the stator and having a free-cutting material, in which a convex portion and a concave portion are alternately formed in an axial direction, on a surface facing the rotor; a plurality of radial fins protruding radially outward from the outer circumferential surface of the rotor; and oblique fins which obliquely protrude from the outer circumferential surface of the rotor toward both ends of the free-cutting material of the sealing ring in the axial direction from the outside of the both ends.

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.

Provided is a sealing component, in particular for sealing a vapor chamber with respect to the surroundings or two vapor chambers having different pressures, including at least one ring- or ring-segment-shaped main body, which is at least substantially U-shaped in cross-section and which has two end-face walls and a lateral wall connecting the two end-face walls, a support structure being provided within the main body, which support structure connects the two end-face walls to each other.