A gas turbine engine rotor assembly, comprising: a shaft about an axis having an outer surface radially outward and a groove radially into the outer surface; a disc surrounding the shaft rotatable with the shaft about the axis, the disc having an inner surface extending axially defining an inner diameter, having a disc profile around the groove and axially away from and radially inwardly of the inner diameter, the shaft and the disc defining a gap circumscribed outwardly by the inner diameter and inwardly by the outer surface; and a seal including a split ring fitted into the groove and rotatable with the shaft about the axis, the ring having a ring profile complementary to the disc profile, the ring resiliently expandable radially in the gap to the inner diameter, the disc profile cooperable with the ring profile to axially load the shaft via the ring expanded across the gap.

A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a bearing compartment, a seal assembly configured to establish a seal of the bearing compartment. The seal assembly includes a seal plate. The gas turbine engine further includes a gutter configured to collect oil slung from the seal plate. The gutter extends only partially around the seal plate. A method is also disclosed.

A seal system has: a first member; a seal carried by the first member and having a seal face; and a second member rotatable relative to the first member about an axis. The second member has: a seat, the seat having a seat face in sliding sealing engagement with the seal face; and a circumferential array of passageway legs. The second member further has an annular channel axially spaced from the seat face, the passageway legs connected to the annular channel.

An assembly is provided for rotational equipment. This assembly includes a seal land and a seal element. The seal land extends circumferentially around and is rotatable about an axial centerline. The seal land includes a seal land surface. The seal element extends circumferentially around the axial centerline. The seal element includes a seal element surface and a seal element passage. The seal element surface is abutted against and is sealingly engaged with the seal land surface. The seal element passage extends through the seal element to an interface between the seal element surface and the seal land surface.

A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a bearing compartment, a seal assembly configured to establish a seal of the bearing compartment. The seal assembly includes a seal plate. The gas turbine engine further includes a gutter configured to collect oil slung from the seal plate. The gutter extends only partially around the seal plate. A method is also disclosed.

A mid-turbine frame for a gas turbine engine includes an inner frame case defining a sealed torque box cavity. Multiple spokes protrude radially outward from the inner frame case, and at least one service line is connected to the inner frame case.

A seal assembly includes a carbon seal that has a sealing surface. A seal seat has a sealing surface and is positioned for rotation relative to the carbon seal. A diamond-like carbon coating at least partially forms the sealing surface on the seal seat.

A seal assembly includes a housing at least partially defining a seal opening and at least partially surrounding a rotatable shaft. A carbon seal is located at least partially in the seal opening and includes a sealing surface. The rotatable shaft includes a radially facing surface that has a carbide based coating and a diamond-like carbon coating in engagement with the sealing surface on the carbon seal.

A seal assembly includes a housing that includes a seal flange at least partially defining a seal opening. A carbon seal is located at least partially in the seal opening and includes a first axially facing surface. The seal flange includes an axially facing surface that has a carbide based coating and a diamond-like carbon coating in engagement with the first axially facing surface on the carbon seal.

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.