A seal assembly includes first, second, and third gas turbine engine components, such as vane assemblies, that are successively arranged around an axis. Each component has first and second mate faces such that the first mate face of the first component and the second mate face of the second component define a first mate face gap, and the first mate face of the second component and the second mate face of the third component to define a second mate face gap. A seal arc segment has first and second seal portions and a connector portion that joins the seal portions. The first seal portion bridges the first mate face gap to seal the first mate face gap, the second seal portion bridges the second mate face gap to seal the second mate face gap, and the connector portion spans circumferentially across the second component.

A turbine seal system comprises a structural frame, a structural member, a seal and a bumper. The structural member is disposed opposite the structural frame. The seal extends between the structural frame and the structural member. The bumper is anchored to the structural frame or the structural member and extends toward a mid-region of the seal. In one embodiment, the structural frame comprises a ring-strut-ring turbine exhaust case.

A turbomachine sealing ring has an axis of revolution and includes an annular support , an annular coating made of abradable material which is carried by the support, and an annular thermal protection plate which is carried by the support. The ring is divided into sectors and has a plurality of ring sectors disposed circumferentially next to one another about the axis. Each ring sector having has a support sector, a coating sector, and a plate sector. Each plate sector having includes a flat tab that is pressed against a face of the corresponding support sector and is fixed to this face by brazing. The tab is inserted into a through-slot in the support sector in order to improve its integrity in operation.

A gas turbine engine has a housing exposed to a high temperature environment. The housing has a circumferential wall extending around the engine centerline and circumscribing an oil cavity. The wall has a sealing interface at an inner diameter thereof, the sealing interface having a central axis offset from the engine centerline. A boss is formed on the wall on the offset side relative to the engine centerline and a probe is mounted to the boss. The probe projects into the oil cavity. The oil in the oil cavity thermally shields the probe from the high temperature environment.

A seal support structure for a turbomachine includes a mounting portion shaped to mount to a stationary structure of a turbomachine and a cylindrical leg portion disposed on the mounting portion extending axially from the mounting portion. The cylindrical leg portion can include a radially extending flange. The flange can extend at an angle of 90 degrees from the end of the cylindrical leg portion. The flange can extend at least partially in an axial direction. The cylindrical leg portion can be formed integrally with the mounting portion. In embodiments, the cylindrical leg portion is not integral with the mounting portion, i.e., the cylindrical leg portion is a separate piece joined to the mounting portion.

A rotating assembly of a gas turbine engine includes a first rotating component; and a second rotating component located radially outboard of the first rotating component, relative to an engine central longitudinal axis. A seal assembly is configured to seal between the first rotating component and the second rotating component. The seal assembly includes a shuttle located on a radial outer surface of the second component and freely axially movable along the radial outer surface and a piston ring seal retained in the shuttle and engaged with the first rotating component. Axial motion of the first rotating component relative to the second rotating component urges movement of the shuttle along the radial outer surface of the second rotating component, while the position of the piston ring seal remains stationary relative to the first rotating component.

A vane arc segment includes an airfoil fairing that has an airfoil wall that defines a fairing platform and a hollow airfoil section. A spar has a spar platform adjacent the fairing platform and a spar leg that extends from the spar platform and through the hollow airfoil section. The spar leg is spaced from the airfoil wall in the hollow airfoil section such that there is a first gap. The spar platform is spaced from the fairing platform such that there is a second gap. A support platform is secured to the spar leg such that the airfoil fairing is trapped between the spar platform and the support platform. There is a spring seal between the spar platform and the fairing platform. The spring seal biases the airfoil fairing toward the support platform and seals the first gap from the second gap.

The invention relates to a shaft seal arrangement, comprising a first seal, a second seal and a third seal which are arranged in series between a product side to be sealed and an atmosphere side, wherein the second seal is arranged between the first seal and the third seal, wherein a first pressure is present in a space adjacent to the second seal in the direction towards the product side, and a second pressure is present in a space adjacent to the second seal in the direction towards the atmosphere side, wherein the space that is adjacent to the atmosphere side is connected to a pressure supply line via which a pressure medium can be supplied into the space, and wherein the first pressure is equal or substantially equal to the second pressure, so that the second seal can be operated with a pressure difference of zero between the first pressure and the second pressure.

An apparatus has: a first member; a shaft rotatable relative to the first member about an axis; and a seal system. The seal system has: a seal carried by the first member and having a seal face; a seal carrier; a seat carried by the shaft and having a seat face in sliding sealing engagement with the seal face; and one or more springs biasing the seal carrier relative to the first member so as to bias the seal face against the seat face. The seal carrier has: an axially-extending wall having an inner diameter (ID) surface; and a radially-extending wall having a first surface. The seal carrier axially-extending wall ID surface has a radially inwardly open groove having a first sidewall and a second sidewall and a base. A wave-form split ring contacts the first sidewall and biases the seal into engagement with the radial wall first surface.

A seal segment has an arcuate body having: a first end; a second end circumferentially opposite the first end; a first face; a second face axially opposite the first face; an inner diameter (ID) face; and an outer diameter (OD) face. The seal segment is shaped to interfit with a plurality of identical seal segments first end to second end to form a seal surrounding a central longitudinal axis. The first face has: a circumferential channel closer to the ID face than the OD face; and a plurality of channels extending from the circumferential channel to the OD face. The ID face has: a circumferential channel closer to the first face than the second face; and a plurality of channels extending from the circumferential channel to the second face. The ID face circumferential channel has an open end.