An apparatus and method of sealing for an engine component between two surfaces arranged in spaced relationship to define a gap. A groove located is located in one of the two surface for receiving a seal having a body with a multi-faceted cross-sectional shape defining multiple seal facets. At least one of the multiple seal facets contacts one or both of the two surfaces.

A sealing element and a rotor of a gas turbine having at least one rotor disc and having an annular rotor component arranged adjacently to the rotor disc and having a plurality of sealing elements arranged distributed around the circumference. The sealing elements are fastened to the rotor disc at least in the axial direction. An inner edge portion of each of the sealing elements is adjacent to a sealing portion of the rotor component. In order to provide a seal between the sealing element and rotor component whilst at the same time enabling a relative axial displacement, a ring seal is arranged in a receiving space formed by the sealing element and rotor component.

A method of limiting circumferential rotation of a split-ring seal for use in a gas turbine engine includes inserting a retention block through a slot in a flange of a support structure and into a groove configured to hold a split-ring seal, and engaging an end of a split-ring seal in the groove with a surface of the retention block.

A static structure of a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an outer platform, an inner platform, an airfoil that extends between the outer platform and the inner platform, a service tube disposed at least partially through the airfoil, and a seal assembly that seals between the service tube and one of the outer platform and the inner platform.

A piston seal assembly for a gas turbine engine includes a seal composed of a nickel-based superalloy; a component in contact with the seal and defining a seal-counterface; and a coating on the seal at the seal-counterface, wherein the coating is a metal alloy binder phase and a hard particle phase distributed through the binder phase.

A gas turbine engine assembly includes a compressor including a plurality of rotors, where at least one of the plurality of rotors includes a radial inner sealing surface. A rotating shaft drives rotation of the plurality of rotors, where the rotating shaft includes an annular groove proximate the radial inner sealing surface. A seal is disposed within the annular groove, and the seal comprises at least two annular sections forming a complete circumference. Each of the at least two annular sections are separate parts and include a radially-facing sealing surface engaged to the radial inner sealing surface of the rotor and an annular slot disposed radially inward of the radially-facing sealing surface. A retainer is disposed within the annular slot limiting radial expansion of the at least two annular sections.

A seal assembly to seal a gas turbine hot gas path flow at an interface of a combustor liner and a downstream component, such as a stage one turbine nozzle, in a gas turbine. The seal assembly including a piston ring seal housing, defining a cavity, and a piston ring disposed within the cavity. The piston ring disposed circumferentially about the combustor liner. The piston ring is responsive to a regulated pressure to secure sealing engagement of the piston ring and outer surface of the combustor liner. The seal assembly includes at least one of one or more sectional through-slots, bumps or channel features to provide for a flow therethrough of a high-pressure (P.sub.high) bypass airflow exiting a compressor to the cavity. The high-pressure (P.sub.high) bypass airflow exerting a radial force on the piston ring.

A carbon seal assembly may comprise a seal support, a seal housing coupled to the seal support, and a carbon seal adjacent an aft portion of the seal housing. The carbon seal may comprise a nose defined by an axial surface of the carbon seal, a first radial surface of the carbon seal, and a second radial surface of the carbon seal radially inward of the first radial surface. The first radial surface and the second radial surface may extend forward from the axial surface. A first axial length of the first radial surface may be greater than a second axial length of the second radial surface.

The disclosure relates to an anti-cavitation device for impeding gas intrusion into oil dampers that support bearings and a rotating shaft. The oil film damper includes an annulus and a pair of piston rings between a structural support and the bearing housing. The piston rings define the axial boundaries of the oil filled annulus. An oil inlet between the pair of piston rings is in communication with a source of pressurized oil. An oil seal is axially spaced from each piston ring defining an annular oil filled reservoir external to each piston ring. The oil seal acts as a one way check valve to impede gas incursion into the oil reservoir and oil filled annulus.

A bearing support may include a central shaft, a flange shaft, and a tube boss. The central shaft may include a central longitudinal axis extending between a first end and a second end of the bearing support. The flange shaft may extend radially outward of the central shaft at an acute angle, relative to the central longitudinal axis from the first end to the second end, and the flange shaft may include a rim defining an aperture. The tube boss extends from the central shaft radially outward through the aperture, according to various embodiments. An annular channel may be between the rim and the tube boss.