A hydrostatic seal assembly includes a primary seal assembly configured to maintain a selected gap between the primary seal and a rotating component, and a seal carrier. The seal carrier includes a radial outer wall, an axial wall extending from the radial outer wall at a first axial end of the radial outer wall, and a carrier arm extending from the radial outer wall at a second axial end of the radial outer wall opposite the first axial end. The carrier arm is secured to a static structure for sealing between the rotating component and the static structure.

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.

A circumferential seal assembly for use between a higher pressure side and a lower pressure side is presented. The seal assembly includes a primary sealing ring, a second sealing ring, a third sealing ring, and an insert. The segmented primary sealing ring sealingly engages both a face sealing surface along a housing and a radial sealing surface along a rotatable element. The insert is disposed within and directly contacts the housing. The second sealing ring is adjacent to the primary sealing ring and sealingly engages both the primary sealing ring and the insert. The segmented third sealing ring contacts and sealingly engages the primary sealing ring opposite the housing. The insert, the second sealing ring, and the third sealing ring cooperate to form a first cavity adjacent to the second sealing ring and the third sealing ring. The primary sealing ring, the second sealing ring, the insert, and the housing cooperate to form a second cavity adjacent to the primary sealing ring. The insert and the second sealing ring separate the first cavity from the second cavity.

A rotary seal assembly for a rotary kiln having a hood and a rotary drum with an opening formed between the drum and the hood, and an end. The rotary seal assembly includes a flexible framework arrangement that attaches to the end. The rotary seal assembly includes a riding surface that engages the drum as the drum rotates. The riding surface includes a series of seal segments with each seal segment having a mounting eye positioned to eliminate a fulcrum point at the mounting eye. The rotary seal assembly includes a seal that is supported by the riding surface and is in essentially 360-degree contact with the drum when it is rotating and seals the opening between the drum when it is rotating in the hood to prevent fluid flow into and out of the end. A rotary seal assembly for a rotary kiln having a hood and a rotary drum with an opening formed between the drum and the hood, and an end, includes redundant tension springs which form a complete 360-degree circle around the drum. A method for sealing an opening formed between a drum and a hood.

A circumferential seal assembly suitable for forming a thin film between a rotatable runner and a sealing ring is presented. The assembly includes an annular seal housing, a rotatable runner, an annular seal ring, and a plurality of groove structures. Each groove structure includes a groove and an optional feed groove. The groove includes at least two adjoining steps defined by base walls arranged to decrease depthwise. Two adjoining base walls are disposed about a base shoulder. Each base shoulder locally redirects a longitudinal flow to form an outward radial flow in the direction of the annular seal ring. The base walls are bounded by and intersect a pair of side walls. A side wall includes side shoulders which narrows the groove widthwise and locally redirects the longitudinal flow to form a lateral flow in the direction of the other side wall. Outward and lateral flows separately or in combination enhance stiffness of a thin-film layer between the annular seal ring and the rotatable runner.

A circumferential sealing assembly for use between a lower-pressure side with a lubricant oil therein and a higher-pressure side with a hot gas therein is presented. The assembly includes a sealing ring interposed between either a rotatable runner and a housing or a sleeve and a housing within a turbine engine. Ducts communicate the hot gas into grooves to form a thin film between the ring and the runner or the ring and the sleeve. First embodiments include grooves on the runner, ducts through the runner, and both grooves and ducts rotating with the runner. Second embodiments include grooves on the ring, ducts through the runner, and ducts rotating with the runner. Third embodiments include grooves on the ring and ducts through the ring adjacent to a runner. Fourth embodiments include grooves on the runner, ducts through the ring, and grooves rotating with the runner. Fifth embodiments include grooves on the sleeve, ducts through the sleeve, and both grooves and ducts rotating with the sleeve. Sixth embodiments include grooves on the ring, ducts through the sleeve, and ducts rotating with the sleeve. Seventh embodiments include grooves on the ring and ducts through the ring adjacent to a sleeve. Eighth embodiments include grooves on the sleeve, ducts through the ring, and grooves rotating with the sleeve.

Provided is a shaft sealing apparatus, which includes a seal ring that is installed in an annular space between a rotor and a stator surrounding an outer circumference side of the rotor, that is formed in a divided structure from a movable seal ring and a stationary seal ring whose circumferential ends are adjacent to each other, and that is configured so that the movable seal ring is biased toward a radial outer side thereof by an elastic body, a seal body that is formed by stacking a plurality of thin seal pieces, which extend from the seal ring toward a radial inner side of the rotor, in a circumferential direction of the rotor, and a communicating part that causes the low-pressure side region and the high-pressure side region to communicate with each other.

A shaft seal mechanism (11) that blocks a fluid (G) flowing within a ring-shaped space (14) is equipped with: a ring-shaped seal housing (21) disposed on a fixed section (12); a plurality of thin-plate seal pieces (22) that are secured to the seal housing (21), are in sliding contact with a rotating shaft (13), and are layered in a ring shape; a ring-shaped high-pressure-side plate (25) that forms a high-pressure-side gap (δH) between itself and the seal housing (21); a ring-shaped low-pressure-side plate (26) that forms a low-pressure-side gap (δL) between the seal housing (21) and the thin-plate seal pieces (22); stepped sections (31, 32) that are formed on side edge sections (22c, 22d) of the thin-plate seal pieces (22); and locking sections (25b, 26b) that lock the stepped sections (31, 32).

A brush seal assembly may include: a packing body configured to be positioned between a rotating body and a fixing body and provided with an insertion groove; a brush seal part configured to include a brush extending toward the rotating body in a state in which one end of the brush seal part is inserted into the insertion groove and a support member supporting the brush; a thermal expansion member configured to adhere to a side of the support member and be thermally expanded in a circumferential direction of the packing body; and a fixing member configured to be fitted in the insertion groove to face the thermal expansion member to simultaneously fix the brush seal part in the circumferential direction and a radial direction of the packing body.

A seal for a gas turbine engine includes a full hoop outer ring, a shoe coupled to the full hoop outer ring via an inner beam and an outer beam, and a wave spring in contact with at least one of the inner beam or the outer beam.