An abradable seal includes a seal element that is formed of a polymer matrix with thermally conductive microspheres dispersed through the polymer matrix. The polymer matrix has a polymer matrix thermal conductivity and the microspheres have a microsphere thermal conductivity that is greater than the polymer matrix thermal conductivity.

Labyrinth seal system includes stationary component and rotatable component, where one of the stationary and rotatable components includes teeth. The labyrinth seal system further includes abradable component coupled to surface of other of the stationary and rotatable components and disposed facing the teeth. The abradable component includes a plurality of honeycomb cells disposed adjacent to each other along axial direction and circumferential direction. Each honeycomb cell includes a plurality of radial sidewalls, where each radial sidewall includes first portion and second portion. The first portion is coupled to the surface and the second portion extends from the first portion towards clearance defined between the stationary and rotatable components. The second portion is bent relative to radial axis of the labyrinth seal system.

What is described is a tree seal for use on a rotating element. The tree seal includes a trunk configured to be coupled to the rotating element. The tree seal also includes a first branch coupled to the trunk and having a first edge configured to form a first mini seal with a housing. The tree seal also includes a second branch coupled to the trunk and having a second edge configured to form a second mini seal with the housing.

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 rotary machine includes turbine moving blades (50); a casing (10) covering the turbine moving blades (50) so as to define a gap at an outer circumferential side of the turbine moving blades; a leaf seal (70) having a seal body (71) that is disposed in the gap so as to protrude radially inward from the casing (10) and is capable of coming into contact with the turbine moving blades (50), and a high-pressure-side plate member (73) that is disposed along a face facing a high pressure side of the seal body (71); and a swirling flow inhibitor (80) that is provided on the high pressure side of the leaf seal (70) in the gap and inhibits a swirl flow flowing through the gap in a circumferential direction.

A centrifugal compressor includes an impeller fixed to a rotary shaft, and a casing accommodating the impeller. The impeller includes a disc-shaped disc portion, a plurality of blade portions provided to be separated from one another in a circumferential direction, and a cover portion facing the disc portion with a gap interposed therebetween and covering the plurality of blade portions from one of two sides in the axial direction. The casing includes a perforated face, which faces the cover portion with a gap interposed therebetween, is provided at an inner peripheral side area in relation to an outer peripheral side end of the cover portion, and is provided with a plurality of holes.

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.

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.