Abstract: A seal assembly includes a rotating seal runner having an outer radial surface, and one or more rotationally stationary seal rings located radially outboard of the seal runner. Each seal ring has an inner radial surface, with the inner radial surface and the outer radial surface defining a sealing interface therebetween. An axially extending shape of the inner radial surface is selected utilizing a predicted shape of the outer radial surface at a selected operating condition of the seal assembly.

Abstract: A seal system for a gas turbine engine includes a seal runner manufactured of a Molybdenum alloy material that provides a first coefficient of thermal expansion and a seal ring manufactured of a graphitic material that provides a second coefficient of thermal expansion greater than the first coefficient of thermal expansion.

Abstract: 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.

Abstract: Apparatus and associated methods relate to a segmented radial seal assembly that includes at least two segments, each segment having a first end and a second end at opposite ends. A first segment first end has a protruding feature and defines a tangential vector from a circumferential ring that is formed by the segmented radial seal. The protruding feature defines a curved face having at least a first axis of curvature that is parallel to the tangential vector. The second segment second end has a recessed feature that is matingly engageable to the first segment first end, thereby forming a first radial seal segment joint. The segmented radial seal assembly is configured to surround a shaft.

Abstract: 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.

Abstract: A seal includes a seal runner, at least one seal ring, and a seal housing. The runner extends in an axial direction to a runner end face that faces a bearing. The ring is fixed to a static structure and has an inner surface engaging the seal runner and a first face that faces the bearing. The seal housing is fixed to the static structure and includes a first portion extending in an axial direction from the first face of the seal ring to a housing face that faces the bearing. The first portion has a first length extending from the first face of the seal ring to the housing face. The seal runner has a first runner portion with a second length that extends from the first face of the seal ring to the runner end face. The second length is at least 35% longer than the first length.

Abstract: 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.

Abstract: 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.

Abstract: A face seal includes a seal carrier defining an axis and having a pilot flange, a seal element disposed at least partially in the seal carrier, and a retaining plate connected to one axial end of the seal carrier. The retaining plate has an axial step disposed circumferentially about the retaining plate. The axial step is interfaced with the pilot flange.

Abstract: A face seal assembly includes a seal. The assembly also includes a seal carrier including a first seal wall, a second seal wall and a base seal wall, the first seal wall, the second seal wall and the base seal wall defining a groove for receiving the seal therein, the second seal wall extending radially outwardly to a non-uniform radial location.

Abstract: A face seal includes a seal carrier defining an axis and having a pilot flange, a seal element disposed at least partially in the seal carrier, and a retaining plate connected to one axial end of the seal carrier. The retaining plate has an axial step disposed circumferentially about the retaining plate. The axial step is interfaced with the pilot flange.

Abstract: A ring seal in a gas turbine engine includes a ring seal body, an axial sealing dam, a radial sealing dam, and at least one bleed slot. The ring seal body is annular in shape and has a first axial side, a second axial side, a radially outer side, and a radially inner side. The axial sealing dam is on the first axial side and is configured to provide a first sealing surface with a first component. The radial sealing dam is on the radially outer side and is configured to provide a second sealing surface with a second component radially outward from the radially outer side. The at least one bleed slot is on the second axial side and configured to allow fluid to pass through when the ring seal is incorrectly oriented such that the at least one bleed slot is adjacent to the first component.

Abstract: A seal assembly for a turbine engine is disclosed and includes a fixed housing including an axial surface defining an inner diameter and an annular seal that is disposed within the housing and seal against a radial surface of the fixed housing. The annular seal includes a first surface transverse to an axis of rotation and a second surface parallel to the axis of rotation defining an inner periphery. The first surface includes a first notch spaced apart from the inner periphery and overlapping the inner diameter of the fixed housing.

Abstract: 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.

Abstract: A ring seal assembly includes a first ring seal that is symmetrical with respect to a radially extending plane. A second ring seal is separated axially from the first ring seal by a spring. The second ring seal includes a first inner circumferential surface. An interference feature extends radially inward from the first inner circumferential surface to a second inner circumferential surface.

Abstract: A force balanced face seal may comprise a seal housing comprising an annular extrusion, a seal support, wherein the annular extrusion is disposed within the seal support, and a primary seal coupled to the seal housing, wherein the primary seal comprises a sealing face and a base opposite the sealing face and proximate the seal housing.

Abstract: A face seal assembly includes a seal. The assembly also includes a seal carrier including a first seal wall, a second seal wall and a base seal wall, the first seal wall, the second seal wall and the base seal wall defining a groove for receiving the seal therein, the second seal wall extending radially outwardly to a non-uniform radial location.

Abstract: A spring guide for use in a seal housing including a first body portion, a second body portion, and a flange portion, including a flange width, extending circumferentially between the first body portion and the second body portion. The flange width being less than or equal to approximately 2.1 millimeters.

Abstract: A ring seal assembly is provided. The ring seal assembly may comprise an air side ring seal and an oil side ring seal. The air side ring seal may have one or more axial and radial grooves. The oil side ring seal may also have one or more axial and radial grooves, and may have circumferential slots in fluid communication with one or more of the grooves. The oil side ring seal may have an extended leg protruding towards the air side ring seal. The extended leg and a forward outer surface of the oil side ring seal and an aft outer surface of the air side ring seal may define a spring cavity.

Abstract: A ring seal in a gas turbine engine includes a ring seal body, an axial sealing dam, a radial sealing dam, and at least one bleed slot. The ring seal body is annular in shape and has a first axial side, a second axial side, a radially outer side, and a radially inner side. The axial sealing dam is on the first axial side and is configured to provide a first sealing surface with a first component. The radial sealing dam is on the radially outer side and is configured to provide a second sealing surface with a second component radially outward from the radially outer side. The at least one bleed slot is on the second axial side and configured to allow fluid to pass through when the ring seal is incorrectly oriented such that the at least one bleed slot is adjacent to the first component.