Abstract: A mounting assembly for a forward end of a liner in a combustor of a gas turbine engine including a dome and a cowl, wherein a longitudinal centerline axis extends through the gas turbine engine. The mounting assembly includes a pin member extending through each one of a plurality of circumferentially spaced openings formed in the forward end of the liner, an aft portion of the cowl, and a portion of the dome, with each pin member including a head portion at one end thereof. A nut is adjustably connected to an end of each pin member opposite the head portion. A bushing is located on each pin member at a position intermediate the head portion and the nut, wherein the openings in the liner forward end are sized to fit around the bushings.

Abstract: An assembly for providing a seal at an aft end of a combustor liner for a gas turbine engine including a longitudinal centerline axis extending therethrough. The sealing assembly includes a substantially annular first sealing member positioned between an aft portion of a support member and the liner aft end so as to seat on a designated surface portion of the liner aft end and a substantially annular second sealing member positioned between the support member aft portion and a turbine nozzle located downstream of the liner aft end so as to seat on a designated surface portion of the support member aft portion. Accordingly, the first sealing member is maintained in its seated position as the support member aft portion moves radially with respect to the liner aft end and the second sealing member is maintained in its seated position as the support member aft portion moves axially with respect to the turbine nozzle.

Abstract: A mounting assembly for an aft end of a liner of a gas turbine engine combustor including a support member, wherein a longitudinal centerline axis extends through the gas turbine engine. The mounting assembly includes a pin member extending through each one of a plurality of circumferentially spaced openings in a portion of the support member for the combustor and into a plurality of partial openings formed in the aft end of the liner, with each pin member including a head portion at one end thereof, and a device positioned within each opening in the support member so as to retain the pin members therein. The pin members and the support member are able to slide radially and/or axially with respect to the liner aft end as the support member experiences thermal growth greater than the liner.

Abstract: At least one shroud segment, floating axially independently of adjacent turbine engine shroud assembly members, includes a segment body comprising a radially outer surface and a radially outwardly projecting segment support that includes an axial support wall surface therein. The assembly includes a shroud hanger in axial juxtaposition with the segment support, and at least one axial support projection from the shroud hanger into the segment support at the support wall surface. The support projection supports the shroud segment releasably at the support wall surface sufficiently to enable relative axial movement of the shroud segment on the support projection independently of the shroud hanger and adjacent engine members.

Abstract: A support assembly for a gas turbine engine combustor including an inner liner and an inner casing spaced therefrom, wherein a longitudinal centerline axis extends through the gas turbine engine. The support assembly includes an annular inner support cone located adjacent an aft end of said inner liner, an annular nozzle support connected to the inner support cone, and a plurality of support members connected at a first end to a forward end of the inner liner and connected at a second end to the inner support cone.

Abstract: An assembly for providing a seal at an aft end of a combustor liner for a gas turbine engine including a longitudinal centerline axis extending therethrough. The sealing assembly includes a substantially annular first sealing member positioned between an aft portion of a support member and the liner aft end so as to seat on a designated surface portion of the liner aft end and a substantially annular second sealing member positioned between the support member aft portion and a turbine nozzle located downstream of the liner aft end so as to seat on a designated surface portion of the support member aft portion. Accordingly, the first sealing member is maintained in its seated position as the support member aft portion moves radially with respect to the liner aft end and the second sealing member is maintained in its seated position as the support member aft portion moves axially with respect to the turbine nozzle.

Abstract: A support assembly for a gas turbine engine combustor including an inner liner and an inner casing spaced therefrom, wherein a longitudinal centerline axis extends through the gas turbine engine. The support assembly includes an annular inner support cone located adjacent an aft end of said inner liner, an annular nozzle support connected to the inner support cone, and a plurality of support members connected at a first end to a forward end of the inner liner and connected at a second end to the inner support cone.

Abstract: A mounting assembly for an aft end of a liner of a gas turbine engine combustor including a support member, wherein a longitudinal centerline axis extends through the gas turbine engine. The mounting assembly includes a pin member extending through each one of a plurality of circumferentially spaced openings in a portion of the support member for the combustor and into a plurality of partial openings formed in the aft end of the liner, with each pin member including a head portion at one end thereof, and a device positioned within each opening in the support member so as to retain the pin members therein. The pin members and the support member are able to slide radially and/or axially with respect to the liner aft end as the support member experiences thermal growth greater than the liner.

Abstract: A mounting assembly for a forward end of a liner in a combustor of a gas turbine engine including a dome and a cowl, wherein a longitudinal centerline axis extends through the gas turbine engine. The mounting assembly includes a pin member extending through each one of a plurality of circumferentially spaced openings formed in the forward end of the liner, an aft portion of the cowl, and a portion of the dome, with each pin member including a head portion at one end thereof. A nut is adjustably connected to an end of each pin member opposite the head portion. A bushing is located on each pin member at a position intermediate the head portion and the nut, wherein the openings in the liner forward end are sized to fit around the bushings.

Abstract: A rotor system for a gas turbine engine is provided having an outer rotor which includes an annular outer spool that comprises at least one ring portion of increased thickness with respect to the remainder of the outer spool, attached to a relatively thinner, axially extending arm portion. A plurality of outer turbine blades are attached to the ring portion of the outer spool and extend radially inwardly into a working gas flowpath of the engine. A casing surrounds the outer spool and defines an annular cavity between the casing and the outer spool, which is sealed by forward and aft brush seals at the forward and aft ends thereof. At least one inlet port is formed through the casing for admitting a flow of cooling air to the annular cavity. Means are provided for directing this cooling air flow to the ring portion of the outer spool.

Abstract: A face seal assembly is provided having an annular seal body mounted in an axially moveable relationship to a seal support structure. A piston ring is disposed between the annular seal body and the seal support structure forming a secondary seal. A first locator spring, which is an annular wave spring, is disposed between said seal support structure and the piston ring to urge the piston ring in an axial direction. Optionally, a second locator spring, also a wave spring, may be disposed between the piston ring and the seal support structure for urging the piston ring in a radial direction.

Abstract: A turbine engine shroud assembly comprises at least one shroud segment floating axially independently of other engine members disposed in adjacent juxtaposition with the shroud segment. In one embodiment, the assembly comprises a plurality of shroud segments, in one form of a low ductility material, disposed in circumferential juxtaposition. Each segment includes a segment body comprising a radially outer surface with which a radially outwardly projecting segment support is attached. The shroud segment support includes therein a support wall surface extending generally axially into and at least partially through the segment support. The assembly includes a shroud hanger in axial juxtaposition with the shroud segment support, and at least one support projection, for example a support pin, extending generally axially from the shroud hanger into the shroud segment support at the shroud segment support wall surface.

Abstract: A turbine engine shroud segment, preferably a low ductility material, for example a ceramic matrix composite, comprises a segment body extending between body circumferential ends. The body includes a body radially inner surface arcuate at least circumferentially, and a body radially outer surface from which a plurality of hooks extend generally radially outwardly. Each hook comprises a generally radially outwardly extending hook arm with a generally axially extending hook end having a generally radially inner surface in spaced apart juxtaposition with a portion of the body radially outer surface. Such body outer surface includes at least two body contact surfaces each matched in shape and in juxtaposition at least at body circumferential ends with a cooperating hanger contact surface. The radially inner surface of each hook end includes a hook end contact surface matched in shape with a cooperating hanger contact surface at least in a circumferential middle portion of such surface.

Abstract: A face seal assembly is provided having an annular seal body mounted in an axially moveable relationship to a seal support structure. A piston ring is disposed between the annular seal body and the seal support structure forming a secondary seal. A first locator spring, which is an annular wave spring, is disposed between said seal support structure and the piston ring to urge the piston ring in an axial direction. Optionally, a second locator spring, also a wave spring, may be disposed between the piston ring and the seal support structure for urging the piston ring in a radial direction.

Abstract: A counterrotatable booster compressor assembly for a gas turbine engine having a counterrotatable fan section with a first fan blade row connected to a first drive shaft and a second fan blade row axially spaced from the first fan blade row and connected to a second drive shaft. The counterrotatable booster compressor assembly includes a first compressor blade row connected to the first drive shaft, a plurality of fan shaft extensions connected to the second drive shaft for driving the second fan blade row, and at least one compressor blade integral with each fan shaft extension so as to form a second compressor blade row interdigitated with the first compressor blade row.

Abstract: A counterrotatable booster compressor assembly for a gas turbine engine having a counterrotatable fan section with a first fan blade row connected to a first drive shaft and a second fan blade row axially spaced from the first fan blade row and connected to a second drive shaft. The counterrotatable booster compressor assembly includes a first compressor blade row connected to the first drive shaft, a plurality of fan shaft extensions connected to the second drive shaft for driving the second fan blade row, and at least one compressor blade integral with each fan shaft extension so as to form a second compressor blade row interdigitated with the first compressor blade row.

Abstract: A turbine engine shroud segment, preferably a low ductility material for example a ceramic matrix composite, comprises a segment body extending between body circumferential ends. The body includes a body radially inner surface arcuate at least circumferentially, and a body radially outer surface from which a plurality of hooks extend generally radially outwardly. Each hook comprises a generally radially outwardly extending hook arm with a generally axially extending hook end having a generally radially inner surface in spaced apart juxtaposition with a portion of the body radially outer surface. Such body outer surface includes at least two body contact surfaces each matched in shape and in juxtaposition at least at body circumferential ends with a cooperating hanger contact surface. The radially inner surface of each hook end includes a hook end contact surface matched in shape with a cooperating hanger contact surface at least in a circumferential middle portion of such surface.

Abstract: A turbine cooling circuit includes a flow sleeve having an aft end for adjoining the rim of a turbine disk. A seal rotor is spaced from the aft end adjacent a row of inlet holes. An inducer has an outlet disposed radially outwardly from the sleeve inlet holes. And, a seal stator surrounds the seal rotor to define a rotary seal disposed radially inwardly from the inducer outlet.

Abstract: A rotor assembly for a gas turbine engine includes a bearing assembly that reduces dynamic loads to a support frame and static bending to the rotor assembly during periods of rotor unbalance. The rotor assembly includes a rotor shaft coupled to a fan and supported longitudinally with a plurality of bearing assemblies on a support frame. A number two bearing assembly includes a paired race, a rolling element, and a mounting race. The mounting race includes a spherical face and is secured to the bearing assembly with a retainer that plastically fails at a pre-determined moment load.

Abstract: A turbine cooling circuit includes a flow sleeve having an aft end for adjoining the rim of a turbine disk. A seal rotor is spaced from the aft end adjacent a row of inlet holes. An inducer has an outlet disposed radially outwardly from the sleeve inlet holes. And, a seal stator surrounds the seal rotor to define a rotary seal disposed radially inwardly from the inducer outlet.