An intershaft seal assembly for use between a rotatable outer structure and an inner structure within a turbine engine is presented. The assembly includes a primary sealing ring, a translatable carrier, a secondary sealing ring(s), a lower-pressure chamber, a higher-pressure chamber, a first channel(s), and a second channel(s). The primary ring is disposed within and extends from a circumferential groove about the carrier so as to sealingly engage the rotatable outer structure. The primary ring rotates within the groove and with the rotatable outer structure. Each secondary ring is interposed between the carrier and the inner structure. The carrier slidingly contacts the secondary ring(s). The lower-pressure chamber is generally defined by the carrier and the inner structure adjacent to a higher-pressure side. The higher-pressure chamber is generally defined by the carrier and the inner structure adjacent to a lower-pressure side. Each first channel traverses the carrier so that a gas from the lower-pressure side may enter the lower-pressure chamber. Each second channel traverses the carrier so that a gas from the higher-pressure side may enter the higher-pressure chamber. The sum of the translation-resistant forces (F.sub.TTR) encountered by the carrier is less than the translation-resistance force (F.sub.TR) encountered by the primary seal ring.

A recessed part formed on a side surface includes a dynamic pressure part extending in the circumferential direction to converge on the side surface, and an introduction part extending from the dynamic pressure to open the dynamic pressure part toward the inner periphery side. One or two inner peripheral wall parts are provided for each of the recessed parts. The inner peripheral wall part is a portion defined on the inner periphery side of the corresponding recessed part by the dynamic pressure part and the introduction part. The inner peripheral wall part includes an inner peripheral wall surface. The inner peripheral wall surface extends toward the introduction part in the circumferential direction with inclining with respect to the side surface such that the inner peripheral wall surface is depressed from the side surface.

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 seal (100) for sealing a lubricant space prevents lubricant (320) escaping. A rolling stand has a seal of this kind. The seal (100) is made at least partially from elastic material. To enable a pressing force FR, with which the bottom face (112) of the seal is pressed against an opposite contact surface (218), for example of a roll journal (212), to be variably set, the seal (100) has at least two cavities, which are separated from each other in the circumferential direction and which are open towards the lubricant space of the bearing.

A sealing structure includes a sealing device including a first seal lip having a first seal-lip end, and a support ring that supports the first seal lip; and a plurality of members that define an attachment space into which the sealing device is attached, the members including an inner peripheral wall arranged on the inner periphery side of the sealing device, a first end wall arranged on one axial end of the sealing device, and a second end wall arranged on another axial end of the sealing device. The first seal-lip end has a certain amount of interference with the inner peripheral wall and the first end wall so that its radial reaction force radially presses the support ring outward and its axial reaction force presses the support ring toward the second end wall.

A seal ring has, on an outer peripheral surface side thereof, a pair of recessed parts 140 extending in a circumferential direction on both sides in a width direction thereof to form a projection part 120 between the pair of recessed parts 140, and has a plurality of ribs 130 connected to the projection part 120 and extending to lateral surfaces of the seal ring at intervals in the circumferential direction inside the pair of recessed parts 140, and a plurality of ribs 130 arranged on a sealed region side among the plurality of ribs 130 have lateral-wall surfaces on an upstream side in a relative rotation direction of a housing with respect to a shaft, each of the lateral-wall surfaces having inclined surfaces inclined from the upstream side to a downstream side in the relative rotation direction of the housing from the projection part 120 toward the lateral surfaces of the seal ring.

An assembly is provided that includes a slider seal having a washer and a tubular puck. The washer includes an inner washer surface and an outer washer surface. The inner washer surface extends around an axis of the slider seal and has a non-circular cross-sectional geometry. The inner washer surface forms a washer bore axially through the washer. The outer washer surface extends around the axis and has a cross-sectional geometry with a shape that is different than a shape of the non-circular cross-sectional geometry. The tubular puck projects axially through the washer bore and includes an outer puck surface. The outer puck surface extends around the axis. The outer puck surface is sealingly engaged with and configured to slide axially along the inner washer surface.

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 seal ring assembly for a rotor shaft includes a seal casing defining a radially inwardly directed channel. The seal ring is disposed in the radially inwardly directed channel of the seal casing. The seal ring is resiliently joined about the shaft to form a seal, and the seal ring comprises an electrically insulating or dissipative material or a non-metallic material.

A bearing compartment seal for a gas turbine engine includes a seal ring that defines an axis and has a radially inward facing sealing surface. A seal runner is configured to rotate relative to the seal ring. The seal runner has a runner surface facing the radially inward facing sealing surface. A plurality of grooves are spaced circumferentially along the runner surface. The plurality of grooves have a length in an axial direction that is at least 50% of an axial length of the runner surface.