Abstract: 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.

Abstract: 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.

Abstract: A gas turbine engine component includes a first flange with a plurality of first jack screw holes and a second flange attached to the first flange. The second flange includes a plurality of second jack screw holes that are concentric with the plurality of first jack screw holes.

Abstract: A sleeve for a bearing damper comprising a cylinder shaped body having a forward end opposite an aft end, the body including an interior surface opposite an exterior surface, the body configured insertable between a bearing proximate the interior surface and a housing proximate the exterior surface; a ring portion proximate the forward end, the ring portion having an outer diameter larger than a diameter of the body; and an extension portion configured to provide an active damper surface extending beyond the housing.

Abstract: A gas turbine engine component includes a first flange with a plurality of first jack screw holes and a second flange attached to the first flange. The second flange includes a plurality of second jack screw holes that are concentric with the plurality of first jack screw holes.

Abstract: A sleeve for a bearing damper comprising a cylinder shaped body having a forward end opposite an aft end, the body including an interior surface opposite an exterior surface, the body configured insertable between a bearing proximate the interior surface and a housing proximate the exterior surface; a ring portion proximate the forward end, the ring portion having an outer diameter larger than a diameter of the body; and an extension portion configured to provide an active damper surface extending beyond the housing.

Abstract: A bearing compartment for a gas turbine engine includes an engine static structure. A rotating structure is configured to rotate about an axis relative to the engine static structure. A bearing supports the rotating structure. A centering spring has first and second rings interconnected by axially extending circumferentially spaced beams. An aperture is provided between an adjacent pair of the beams. The first ring is mounted to the engine static structure. The bearing is mounted to the second ring. The first ring includes multiple circumferentially spaced lugs. Each of the lugs axially extend into a corresponding one of the apertures. The lugs include a support surface that engages the engine static structure.

Abstract: A system is provided that includes a support structure and a nozzle. The support structure includes a cavity surface and an aperture. The cavity surface at least partially forms a boundary of a cavity. The aperture extends partially into the support structure from the cavity surface. The nozzle includes a mount, a neck and a head. The mount is seated within the aperture. The neck is connected to the mount and extends axially along a centerline away from the surface to the head. The head is configured to inject fluid out of the nozzle and into the cavity.

Abstract: A bearing assembly comprises a housing that includes a first housing surface and a second housing surface. The first and second housing surfaces are substantially axially parallel with respect to a rotor centerline. The bearing assembly also comprises a damped outer race that includes a first outer race surface radially adjacent to and opposing the first housing surface which is located radially interior to the first outer race surface. A second outer race surface is radially adjacent to and opposing the second housing surface which is located radially exterior to the second outer race surface. The housing comprises an oil passage that is configured to provide oil from an outlet to a first space between the first outer race surface and the first housing surface, and configured to provide oil to a second space radially between the second outer race surface and the second housing surface.

Abstract: A carbon seal assembly for a gas turbine engine is disclosed. The carbon seal assembly includes a first carbon seal. The carbon seal assembly also includes a first carbon seal spring configured to provide force against the first carbon seal in a first axial direction, the first carbon seal spring having an annular shape and circumferentially disposed around a first shaft of the gas turbine engine.

Abstract: An assembly is provided for a piece of rotational equipment with an axis. This assembly includes a static structure, a bearing within a bore of the static structure, and a centering spring mounting the bearing to the static structure. The static structure is configured with the bore, a slot, a first slot surface and a second slot surface. The slot extends radially into the static structure from the bore. The slot extends axially within the static structure between the first slot surface and the second slot surface. The centering spring includes an annular hub and a mounting tab. The annular hub is within the bore. The mounting tab projects radially from the annular hub into the slot.

Abstract: A carbon seal assembly for a gas turbine engine is disclosed. The carbon seal assembly includes a first carbon seal. The carbon seal assembly also includes a first carbon seal spring configured to provide force against the first carbon seal in a first axial direction, the first carbon seal spring having an annular shape and circumferentially disposed around a first shaft of the gas turbine engine.

Abstract: An assembly is provided for a piece of rotational equipment with an axis. This assembly includes a static structure, a bearing within a bore of the static structure, and a centering spring mounting the bearing to the static structure. The static structure is configured with the bore, a slot, a first slot surface and a second slot surface. The slot extends radially into the static structure from the bore. The slot extends axially within the static structure between the first slot surface and the second slot surface. The centering spring includes an annular hub and a mounting tab. The annular hub is within the bore. The mounting tab projects radially from the annular hub into the slot.

Abstract: A system is provided that includes a support structure and a nozzle. The support structure includes a cavity surface and an aperture. The cavity surface at least partially forms a boundary of a cavity. The aperture extends partially into the support structure from the cavity surface. The nozzle includes a mount, a neck and a head. The mount is seated within the aperture. The neck is connected to the mount and extends axially along a centerline away from the surface to the head. The head is configured to inject fluid out of the nozzle and into the cavity.

Abstract: An assembly includes a centering spring having an annular flange, an annular body, and a plurality of resilient beams extending from the flange to the body. The annular flange defines a passage that extends at least radially inward with respect to a centerline circumscribed by the flange from a radially outer surface of the flange to a radially inner surface of the flange. The annular body is spaced from the flange along the centerline, a radially outer surface of the body forming a first annular cavity relative to an adjacent surface configured to be a first fluid damper. A deflection of the body relative to the flange is restrained by a restoring force produced by the plurality of resilient beams and the first fluid damper. A method includes providing the aforementioned assembly and passing a damping fluid through the passage of the flange.

Abstract: An assembly includes a centering spring having an annular flange, an annular body, and a plurality of resilient beams extending from the flange to the body. The annular flange defines a passage that extends at least radially inward with respect to a centerline circumscribed by the flange from a radially outer surface of the flange to a radially inner surface of the flange. The annular body is spaced from the flange along the centerline, a radially outer surface of the body forming a first annular cavity relative to an adjacent surface configured to be a first fluid damper. A deflection of the body relative to the flange is restrained by a restoring force produced by the plurality of resilient beams and the first fluid damper. A method includes providing the aforementioned assembly and passing a damping fluid through the passage of the flange.