A ring seal assembly includes a first seal seat, a second seal seat axially abutting the first seal seat and two or more seal rings located axially between the first seal seat and the second seal seat. One or more pilot features are positioned at one or more of the first seal seat or the second seal seat to radially locate a ring seal of the two or more seal rings during assembly of the ring seal assembly. A method of installing a ring seal assembly includes securing a first seal seat at a rotating component, inserting a first seal ring onto the first seal seat, and installing a second seal ring and a second seal seat to the rotating component. The second seal ring is guided into a selected radial position via one or more pilot features located at the first seal seat and/or the second seal seat.

An assembly is provided for rotational equipment. This assembly includes a stationary structure, a rotating structure, a seal element and an anti-rotation lock. The rotating structure is rotatable about an axis. The rotating structure is configured as or otherwise includes a seal land. The seal element is configured to seal a gap between the stationary structure and the seal land. The seal element extends circumferentially about the axis. The seal element axially contacts the seal land. The anti-rotation lock projects radially into the stationary structure and the seal element. The anti-rotation lock is configured to at least substantially prevent rotation of the seal element relative to the stationary structure.

A bearing compartment seal for a gas turbine engine includes at least one seal ring defining an axis and having a radially inward facing sealing surface and a seal runner having a support constructed of a first material and an interface portion constructed of a second material. The interface portion includes a radially outward facing surface. A first coefficient of thermal expansion of the second material is at most approximately equal to a second coefficient of thermal expansion of the at least one seal ring.

A turbocharger includes: a turbine wheel; a turbine housing; a bearing housing; a shroud having a facing surface which faces a tip of a blade of the turbine wheel and being configured to surround the turbine wheel, the shroud comprising a separate member from the turbine housing and being disposed inside the turbine housing via a gap with respect to the turbine housing; a mount supported to at least one of the turbine housing or the bearing housing, at a position closer to the bearing housing than a scroll flow path in an axial direction of the turbine wheel; and at least one connection part connecting the mount and the shroud.

A seal assembly includes a first and second seats. The first seat includes an axial portion extending circumferentially around a center axis and extending axially from a first end to a second end. A radial portion extends circumferentially around the axial portion and extends radially from the axial portion between the first end and the second end. A cavity is formed in the radial portion and extends circumferentially around the axial portion. A second seat includes a radial segment extending circumferentially around the center axis and extending radially from an inner surface to an outer surface of the radial segment. An axial segment extends circumferentially around the first end of the first seat, and extends axially from the radially segment to a distal end. The axial segment includes a tapered outer surface that tapers radially inward toward the distal end. The distal end is received in the cavity.

A gas turbine engine includes a compressor section having multiple stages, a combustor section fluidly connected to the compressor section, a turbine section fluidly connected to the combustor section, and a bleed structure radially outward of the stages. The bleed structure includes a body structure having a first set of openings radially outward of a first stage and a second set of openings radially outward of a second stage. The bleed structure further includes a circumferential sleeve configured to cover the first set of openings in a first position and configured to cover the second set of openings in a second position. An actuator is coupled to the circumferential sleeve and is configured to articulate the sleeve between the first and second positions.

A ring seal assembly includes a first seal seat, a second seal seat axially abutting the first seal seat and two or more seal rings located axially between the first seal seat and the second seal seat. One or more pilot features are positioned at one or more of the first seal seat or the second seal seat to radially locate a ring seal of the two or more seal rings during assembly of the ring seal assembly. A method of installing a ring seal assembly includes securing a first seal seat at a rotating component, inserting a first seal ring onto the first seal seat, and installing a second seal ring and a second seal seat to the rotating component. The second seal ring is guided into a selected radial position via one or more pilot features located at the first seal seat and/or the second seal seat.

A gas turbine engine includes a rotor that that has a seal surface, a shaft that has an annular seal channel that opens to the seal surface, and a seal disposed in the annular seal channel for sealing against the seal surface. The seal is made of a composite having carbon fibers disposed in a carbon matrix.

An internal combustion engine, ICE, system, includes a turbocharger having a turbine and a compressor for compressing intake air and feeding the intake air to the ICE. A turbo turbine unit is disposed in an exhaust gas path downstream the turbocharger to receive exhaust gas from the turbocharger. The turbo turbine unit having a turbine wheel, a bearing housing defining an inside volume for containing lubrication oil, and a sealing arrangement positioned in the vicinity of the turbine wheel for preventing lubrication oil from escaping from the inside volume of the bearing housing to an exhaust duct of the turbo turbine unit. A buffer air conduit extends between a selected position at the compressor and a buffer air inlet of the turbo turbine unit. The buffer air inlet is in fluid communication with a buffer air channel inside the turbo turbine unit to direct buffer air to a position in-between axially opposite arranged annular sealing members to provide a counter-pressure against at least one of the annular sealing members.

A gas turbine engine includes a compressor section having multiple stages, a combustor section fluidly connected to the compressor section, a turbine section fluidly connected to the combustor section, and a bleed structure radially outward of the stages. The bleed structure includes a body structure having a first set of openings radially outward of a first stage and a second set of openings radially outward of a second stage. The bleed structure further includes a circumferential sleeve configured to cover the first set of openings in a first position and configured to cover the second set of openings in a second position. An actuator is coupled to the circumferential sleeve and is configured to articulate the sleeve between the first and second positions.