An air conditioning rotating body includes a rotor having a cylindrical shape, and a labyrinth seal structure. The rotor is housed in a casing so as to be freely rotatable. The air conditioning rotating body treats air passing through the rotor in an axial direction. The labyrinth seal structure is provided between an outer circumferential portion of the rotor and the casing. The labyrinth seal structure includes a first protrusion protruding in the axial direction from the rotor toward the casing, and a second protrusion protruding in the axial direction from the casing toward the rotor.

A combined sealing device with magnetic fluid includes a housing having a chamber; a rotating shaft rotatably arranged in the chamber; a seal assembly fitted over the rotating shaft and located in the chamber, in which the seal assembly includes a brush seal part, a magnetic fluid seal part, and a labyrinth seal part all fitted over the rotating shaft and spaced apart from one another in an axial direction of the rotating shaft, the brush seal part being arranged adjacent to the sealing cavity, and the magnetic fluid seal part being arranged between the brush seal part and the labyrinth seal part; and an absorption part arranged in the brush seal part and configured to adsorb a sealing medium spilled from the sealing cavity.

Fluid transfer seal assemblies for transferring process fluid between a stationary component and a rotating component, fluid transfer systems, and methods for transferring process fluid between the stationary and rotating components via a fluid transfer assembly are provided. A rotatable component includes a sealing surface. The fluid transfer seal assembly comprises a face seal ring having at least one segment of a fluid passageway and a sealing face configured to be disposed opposite of the sealing surface. The sealing face or the opposed sealing surface includes a geometric feature for forming a hydrodynamic seal therebetween. A secondary seal is configured to be disposed between and contacting the face seal ring and the stationary component.

A seal member (7) is provided between a combustor disposed around a rotor axis and a vane disposed on the downstream side in an axial direction and defining a part of a combustion gas flow passage (Pg) through which combustion gas (G) flows, and seals a gap between the combustor and the vane. The seal member (7) has: an end face (71a) that faces the downstream side in the axial direction so as to face a lateral end face (461) of the vane facing the upstream side in the axial direction; cooling channels (80) through which cooling air is discharged from a plurality of openings (80a) provided in the end face (71a) in an array in a circumferential direction based on the rotor axis; and a clearance forming portion (71b) that protrudes further toward the downstream side in the axial direction than the end face (71a) in which the openings are formed.

A sealing structure for a front cover of an engine includes a front cover made of resin of an engine in which a through-hole, into which a boss part of a torsional damper is to be inserted, is provided, and a sealing apparatus to seal between the through-hole of the front cover and the shaft part. The sealing apparatus includes a support ring that is made of resin and has an annular shape, and an elastic body part that is made of an elastic material, has an annular shape and is attached to the support ring. The elastic body part has an annular seal lip that contacts the shaft part such that the shaft part is able to slide, and the support ring is bonded to the front cover.

A seal assembly includes a housing defining a bore and a shaft received in the bore. A seal member is secured to the housing for sealing a gap between the housing and the shaft. A slinger is secured to the shaft. The slinger being made from plastic and including a first semi-circular part and a second semi-circular part that is secured to the first semi-circular part. The slinger includes a radially extending wall portion with a raised bumper feature at a radially outer surface opposing the seal member. The slinger further includes an axially protruding labyrinth feature extending from the radially extending wall portion and toward the seal member. The first semi-circular part and the second semi-circular part can be snap fit to one another.

A turbine section has: a rotor rotatable about a central axis, the rotor having blades each protruding radially outwardly from a platform relative to the central axis; a stator having vanes each protruding radially outwardly from a shroud; a rim seal between the platform and the shroud, the rim seal having: an axial overlap between the platform and the shroud, and a lip protruding in a direction having a radial component relative to the central axis from one of the platform and the shroud toward the other of the platform and the shroud, the lip axially overlapping the other of the platform and the shroud, the lip having a radial height such that a radial gap remains between the lip and the other of the platform and the shroud when the turbine section is in operation.

A seal structure includes: a first member and a second member disposed so as to face a combustion gas flow passage; a third member disposed on the outer side of the combustion gas flow passage; a heat-resistant coating formed on at least one of a first end face and a second end face, on the side of the face closer to the combustion gas flow passage; and a contact part disposed in the first end face and the second end face, further on the outer side than the heat-resistant coating. When the first member and the second member move relatively toward each other, the contact part restricts the relative movement by coming in contact in a state where a clearance is left between the heat-resistant coating and the face facing the heat-resistant coating.

A rotary device includes: a housing; an impeller disposed in the housing; a rotor disposed in the housing and configured to drive the impeller; and a labyrinth seal disposed between the impeller and the rotor in the housing and configured to control an amount of air injected through the impeller to cool the rotor. A flow path opening that penetrates through the rotor is formed inside the rotor along a rotational axis of the rotor and the labyrinth seal comprises a teeth portion having a predetermined number of steps provided in the labyrinth seal.

A turbine vane includes a blade body and a shroud. The shroud includes a gas path surface, a front end surface, a front end corner portion which is a corner portion between the gas path surface and the front end surface, a cavity defining surface which defines a cavity allowing cooling air to flow thereinto, a first air passage in which the cooling air flows, and a second air passage in which the cooling air flows. The first air passage includes a first inlet opened at the cavity defining surface and a first outlet opened at the front end corner portion. The second air passage includes a second inlet opened at the cavity defining surface and a second outlet opened at the front end surface.