A seal assembly is disclosed for sealing a high pressure fluid cavity from a low pressure fluid cavity. The cavities are at least partially disposed between a rotatable shaft and a sump housing. The seal assembly comprises a circumferential runner and a seal ring. The circumferential runner is carried by the shaft and has a radially outward facing seal surface extending axially along the shaft. The seal ring is sealing engaged with the sump housing and has a radially inward facing seal surface that sealingly engages the radially outward facing seal surface of the runner. The runner and the seal ring are formed from materials having coefficients of thermal expansion that are matched to effect sealing engagement between the runner and the seal ring over a predetermined range of operating temperatures.

Provided is a seal device configured to prevent leakage of a fluid on an outer circumferential surface of a rotary shaft in a direction along an axis of the rotary shaft. The seal device includes an annular main body section disposed in a circumferential direction of the rotary shaft, and a plurality of at least two kinds of holes formed in an inner circumferential surface of the main body section opening and facing to the outer circumferential surface of the rotary shaft, and having different depths.

A low drag fluid seal. The fluid seal includes a rigid lip separated from the rotor shaft by a gap, the gap being sufficient narrow, radially, to prevent liquid from seeping through the gap at an unacceptable rate, but sufficiently wide, radially, to avoid unacceptably high viscous drag. Fluid that seeps through the gap accumulates in a recovery cavity and is recovered by a scavenge pump.

A low drag fluid seal. The fluid seal includes a rigid lip separated from the rotor shaft by a gap, the gap being sufficient narrow, radially, to prevent liquid from seeping through the gap at an unacceptable rate, but sufficiently wide, radially, to avoid unacceptably high viscous drag. Fluid that seeps through the gap accumulates in a recovery cavity and is recovered by a scavenge pump.

The invention relates to a sealing arrangement 15, a guide vane arrangement, and a turbomachine 11 with such a sealing arrangement 15, wherein the sealing arrangement 15 is designed for a guide vane ring 60 of a turbomachine 11, wherein the sealing arrangement 15 comprises a thin-walled annular structure 80 that is substantially closed on all sides, and wherein the annular structure 80 delimits an annular interior space 105, wherein a hollow cell structure 109, which is designed so as to mechanically support the annular structure 80, is provided in the annular interior space 105.

Various embodiments include gas turbine seals and methods of forming such seals. In some cases, a turbine includes: a first arcuate component adjacent to a second arcuate component, each arcuate component including one or more slots located in an end face, each of the one or more slots having a plurality of axial surfaces and radially facing surfaces extending from opposite ends of the axial surfaces and a seal assembly disposed in the slot. The seal assembly including a backup intersegment seal disposed in the slot on a high-pressure side of the slot and a shim seal disposed in the slot over the backup intersegment seal and covering the backup intersegment seal on a low-pressure side of the slot. The shim seal including one or more shim seal segments and having a gap formed between each of the one or more shim seal segments.

A blade outer airseal has a body comprising: an inner diameter (ID) surface; an outer diameter (OD) surface; a leading end; and a trailing end. The airseal body has a metallic substrate and a coating system atop the substrate along at least a portion of the inner diameter surface. At least over a first area of the inner diameter surface, the coating system comprises an abradable layer and a thermal barrier layer between the abradable layer and the substrate; and the thermal barrier layer comprises a ceramic and metallic phases within the ceramic.

A blade outer airseal has a body comprising: an inner diameter (ID) surface; an outer diameter (OD) surface; a leading end; and a trailing end. The airseal body has a metallic substrate and a coating system atop the substrate along at least a portion of the inner diameter surface. At least over a first area of the inner diameter surface, the coating system comprises an abradable layer and a thermal barrier layer between the abradable layer and the substrate; and the thermal barrier layer comprises a ceramic and metallic phases within the ceramic.

A labyrinth seal for sealing a sealing region between a rotor and stator of a rotary machine includes, a base, and a plurality of sealing rings. The sealing rings are formed on the base, project into the sealing region and form, between them labyrinth valleys bounded, laterally, by the sealing rings and, in the floor of the valleys, by the base. The sealing rings, in at least one region, include at least one material which is different from that of the base.

A non-contact seal assembly for sealing a circumferential gap between a first machine component and a second machine component which is rotatable relative to the first machine component about a longitudinal axis is provided. The non-contact seal assembly includes a seal carrier, a primary seal that includes a plurality of shoes, a mid plate, a secondary seal, and a front plate. The secondary seal may comprise a plurality of sealing segments. The non-contact seal also includes a plurality of damping elements to damp vibrations of the primary seal during operation.