A seal runner assembly for a gas turbine engine includes a non-rotational annular wear seal, and an annular seal runner having an annular body defining an annular front face contacting the wear seal, the annular body defining an aperture extending axially through the seal runner, the aperture configured for receiving therein a part of a shaft of the gas turbine engine, the seal runner having a plurality of axially-extending slots at locations that are distributed around a wall of the seal runner that extends circumferentially about at least a portion of the annular front face and extends from the front face in a direction away from the wear seal. A method for sealing a gap between a part of a machine and a rotatable shaft of the machine is also provided.

A hydrostatic seal assembly includes a primary seal configured to maintain a selected gap between the primary seal and a rotating component. The primary seal includes a seal support, a seal shoe, and one or more seal beams operably connecting the seal support to the seal shoe. The one or more seal beams are configured as spring elements integral with the seal shoe to allow radial movement of the seal shoe relative to the seal support. A seal carrier including a radial outer wall is configured to radially position the primary seal. The seal carrier is configured for a non-contact relationship with the seal shoe during operation of the hydrostatic seal assembly.

A face seal assembly includes a first and a second metallic sealing ring having a common center axis, and each including an outer ring surface and an inner ring surface. A non-metallic sealing element is positioned upon the outer ring surface. The metallic sealing ring also includes a sealing face facing an axially outward direction and extending circumferentially around the center axis in a path that varies from parallelism with a plane normal to the center axis. A stiffness relief groove extends inwardly from the inner ring surface and circumferentially around the center axis and forms an annular spring zone of reduced material thickness to compensate for the varying of the path of the sealing face. One machine system application includes a final drive in a ground-engaging machine.

The invention relates to a mechanical seal assembly, comprising: a mechanical seal (10) including a rotating mechanical sliding ring (2) and a stationary mechanical sliding ring (3), defining a sealing gap (4) between them, a sliding ring carrier (5) arranged at the rotating mechanical sliding ring (2), at least one driver element (6) arranged between the rotating mechanical sliding ring (2) and the sliding ring carrier (5) and provided for transmitting a torque from the sliding ring carrier (5) to the rotating sliding ring (2), wherein the rotating sliding ring (2) is clearance-fitted into the sliding ring carrier (5), wherein the rotating sliding ring (2) comprises a first recess (20), wherein the sliding ring carrier (5) comprises a second recess (50), and wherein the driver element (6) is clearance-fitted into the first recess (20) and is clearance-fitted into the second recess (50).

A mechanical seal, which seals a sealed fluid by interposing an intermediate ring between a rotating ring and a stationary ring, includes a first annular effective seal portion where the rotating ring and the intermediate ring slide with each other and a second annular effective seal portion where the stationary ring and the intermediate ring contact with each other. A load receiving portion is arranged between the intermediate ring and the stationary ring in opposition to a side of the sealed fluid across the sealed fluid of the second annular effective seal portion in a radial direction.

A magnetic seal assembly comprises a metallic annular wear seal. A magnetic seal has a magnetic annular body adjacent to and attracting the wear seal into contact against a contact face thereof. A retainer ring is connected to a surface to the magnetic seal, the retainer ring having a coefficient of thermal expansion different than a coefficient of thermal expansion of the annular body, the coefficient of thermal expansion of the retainer ring selected to constrain a thermal expansion of the annular body. A method for controlling a thermal expansion of a magnetic seal assembly is also provided.

A turbomachine and a method of operating the turbomachine are disclosed. The turbomachine includes a stator, a rotor including a rotor bearing face, and a face seal assembly including a first segmented seal ring and a second segmented seal ring. The first segmented seal ring includes a plurality of joints and a first flat-contact surface and the second segmented seal ring includes a plurality of segment ends and a second flat-contact surface. One of the first and second segmented seal rings includes a seal bearing face. The second segmented seal ring is coupled to the first segmented seal ring such that the second flat-contact surface is in contact with the first flat-contact surface. The plurality of segment ends is circumferentially offset from the plurality of joints. The first segmented seal ring is slidably coupled to the stator and defines a face seal clearance between the rotor and seal bearing faces.

A face seal assembly includes a first and a second metallic sealing ring having a common center axis, and each including an outer ring surface and an inner ring surface. A non-metallic sealing element is positioned upon the outer ring surface. The metallic sealing ring also includes a sealing face facing an axially outward direction and extending circumferentially around the center axis in a path that varies from parallelism with a plane normal to the center axis. A stiffness relief groove extends inwardly from the inner ring surface and circumferentially around the center axis and forms an annular spring zone of reduced material thickness to compensate for the varying of the path of the sealing face. One machine system application includes a final drive in a ground-engaging machine.

A method for preparing a seal assembly for a gas turbine engine, comprising a seal comprising a carbon material; and a seal seat positioned for rotation relative to the seal, wherein the method comprises the steps of: pre-filming a sealing surface of the seal seat with a carbon-based tribofilm; and assembling the seal seat relative to the seal in a gas turbine engine.

The invention relates to a mechanical seal arrangement, comprising a rotating slide ring (2) and an stationary slide ring (3), which delimit a sealing gap (4) in between them, wherein the rotating slide ring (2) has a radially inward facing ledge (20) with a contact surface (21), a bellows element (10) for refitting the rotating slide ring (2) in an axial direction (X-X) of the mechanical seal arrangement, and a release protection device (5) for the rotating slide ring (2), wherein the release protection device (5) comprises an inner sleeve (6) with a radially outward facing web (60) that restricts a movement of the rotating slide ring (2) in the axial direction (X-X), and wherein the rotating slide ring (2) is arranged on the inner sleeve (6) so as to be freely movable in the axial direction (X-X).