Abstract: An improved sealing mechanism for a turbomachine such as a compressor for a gas turbine engine employs an abradable coating with a solid lubricant and metal alloy having a quasicrystalline phase.

Abstract: A device is described for reducing the sealing gap between a rotating component and a stationary component (1, 2) inside a rotary turbo-engine through which a flow passes axially and in which the rotating component (1) and the stationary component (2) each have a surface portion (3, 4) arranged separated by a sealing gap (5) and providing sealing structures on at least one of the two surface portions (3, 4), one of the sealing structures being an abradable planar sealing structure.

Abstract: An air seal for use in a gas turbine engine is disclosed. The seal includes a seal substrate, and an abradable layer on the substrate, with the abradable including a thermoset polymer and a thermoplastic polymer. The abradable may also include a filler to add porosity, or provide lubrication, to enhance abradability.

Abstract: An abradable material for use at moderate temperatures which is particularly suited for use in the compressor sections of gas turbine engines. Abradable seals of the invention comprise an abradable silicone polymer matrix which contains a dispersion of hard abradable organic filler particles.

Abstract: A rotor shaft of a steam turbine is provided with a dovetail-shaped groove. A plurality of inserts are received in the groove through an entry slot at a predetermined circumferential location. Each insert has a sealing surface which, when all inserts are disposed in the groove, form a continuous sealing surface about the rotor shaft. Pins are employed to retain the final insert and, hence, all inserts in the groove by connecting the final insert either to the rotor shaft or to adjacent inserts. In this manner, heat generated by the brush seal bristles bearing on proud portions of the rotor sealing surface is substantially uniformly distributed about the inserts prior to any heat transfer to the rotor. To the extent heat is transferred to the rotor, the temperature distribution is substantially uniform whereby bowing of the rotor due to differential circumferential heating by brush seal contact with proud portions of the rotor is avoided.

Abstract: A honeycomb structure seal is provided for the casing of a turbine, particularly a gas turbine, having a base plate facing the casing wall as well as a brush-against section facing the tips of the turbine rotor blades. The seal includes a multi-layered construction such that the base plate is adjoined by an air-evacuated honeycomb structure section which is therefore insulating in partial areas by a vacuum and which is covered by an intermediate plate, on whose side facing away from the honeycomb structure section the brush-against section is arranged. The intermediate plate is soldered to the honeycomb structure section under vacuum conditions. The brush-against section can also be constructed as a honeycomb seal, in which case the honeycomb cells of the honeycomb structure section have a significantly larger partial surface than the honeycomb cells of the brush-against section.

Abstract: An abradable seal is provided utilizing a laser to cut a pattern into the surface effective to improve abradability in the area of the pattern.

Abstract: A metallic coating containing hard carbide particles is described. The coating is applied by an HVOF process using powder particles whose size ranges from about 15 to about 44 microns. The carbide particles are held in a 80% nickel-20% chromium matrix. The coating has a reduced tensile compressive stress relative to similar plasma sprayed coatings and exhibits a high strain to cracking value.

Abstract: An annular seal is provided between a turbine rotor disc and the adjacent static structure. The seal comprises rotor fins extending from the turbine disc for rotation therewith and an abradable honeycomb layer radially outward of the rotor fins. The abradable honeycomb layer is located on the inner diameter of a sealing ring attached to the static structure. The sealing ring is moveable in an axial direction so that in operation the honeycomb has one axial position for transient conditions and an alternative axial position for stabilized running. The seal clearance can thus be optimised at the two axial positions reducing the leakage flow through the seal.

Abstract: A brush seal segment useful, when circumferentially arrayed with other such segments, to seal the gap between a rotor and a surrounding casing of a rotary machine such as a steam turbine. An annular backing plate has a rim radially-inwardly bounding together upstream-facing and downstream-facing surfaces. Canted bristles abut the upstream-facing surface. The rim is designed to allow the bristles to recover from a rotor rub. In one design, the rim acts as a labyrinth-seal tooth and is shaped to deform, under a radial force, longitudinally away from the upstream-facing surface. In another design, the rim has a more-inwardly projecting second portion near a radially-aligned edge, and only this second portion acts as a labyrinth-seal tooth.

Abstract: A brush gasket for two co-operating components located opposite one another. The brush gasket has a carrier body for the brushes arranged on one of the two components to be sealed off relative to one another, for example, a stator and a rotor. The carrier body has a supporting wall for the brushes on the low-pressure side, in order to protect them against pressure-related deformation. On the second of the components, opposite the carrier body, there is an abrasion ring made of a material which is softer than the material of the brushes. The abrasion ring together with the brushes thus forms a gasket group.

Abstract: An abradable seal is provided utilizing a laser to cut a pattern into the surface effective to improve abradability in the area of the pattern.