A leakage management assembly for an orifice configured to limit a flow of at least one of a leakage fluid and a cooling fluid past an instrument positioned within the orifice are provided. The leakage management assembly includes a labyrinth ferrule including an annular ferrule body having a central bore extending therethrough. The labyrinth ferrule further includes an annular assembly cone formed at a first end of the labyrinth ferrule. The annular assembly cone includes an annular convergent lip and is configured to facilitate directing the instrument into the central bore. The labyrinth ferrule also includes a plurality of labyrinthine annular restrictions extending from a radially inner surface of the annular body toward the central bore. A combustor and a gas turbine engine including such a seal assembly are also provided.

A flex joint (22) includes a bellows (33) and a liner system (46) disposed in the bellows. The liner system includes two generally cylindrical liner pieces (50,52) that are connected to each other in an articulated joint (54). One of the two generally cylindrical liner pieces defines a ball joint end (56) and the other of the two generally cylindrical liner pieces defines a socket joint end (58). The ball joint end is engaged with the socket joint end to form a ball and socket joint as the articulated joint.

An apparatus and method for a turbine engine comprising an outer casing having a first surface and defining an axial centerline and an inner casing located within the outer casing and having a second surface spaced. The first and second surfaces are spaced from each other and define an annular channel between where a combustion air flows in a fore to aft direction along a profile.

A gas turbine engine includes a core engine having a working gas annulus which ends in a core exhaust nozzle for exit of hot gas from the core engine. The engine further includes a bypass duct which ends in a bypass exhaust nozzle for exit of bypass air from the bypass duct, the bypass exhaust nozzle being forward of the core exhaust nozzle, and the bypass duct having an inner wall which forms a surrounding cowl of the core engine and ends at the bypass exhaust nozzle. The engine further includes a core cowl after-body which provides a frustoconical air-washed surface continuing unbroken, on a longitudinal section through the engine, the line of the bypass duct inner wall downstream of the bypass exhaust nozzle. The air-washed surface of the core cowl after-body has plural axially-spaced circumferentially extending corrugations which locally disturb the flow of air over the surface.

A geared turbofan engine includes a fan rotatable about an engine axis. A compressor section compresses air and delivers the compressed air to a combustor where the compressed air is mixed with fuel and ignited to drive a turbine section that in turn drives the fan and the compressor section. A gear system is driven by the turbine section for driving the fan at a speed different than the turbine section. The gear system includes a carrier attached to a fan shaft. A plurality of planet gears are supported within the carrier. Each of the plurality of planet gears includes a first row of gear teeth and a second row of gear teeth supported within the carrier. A sun gear is driven by a turbine section. The sun gear is in driving engagement with the plurality of planet gears. At least two separate ring gears circumscribe the plurality of planet gears. Each of the at least two ring gears are supported by a respective flexible ring gear mount that enables movement relative to an engine static structure. A fan drive gear system for a gas turbine engine is also disclosed.

A variable turbine geometry (VTG) turbocharger is disclosed. The VTG turbocharger may comprise a turbine section, a bearing section, and an actuation pivot shaft (APS) having a bearing side in the bearing section and a pressure side in the turbine section. The VTG turbocharger may further comprise a bushing surrounding the APS and extending from a first end at the pressure side to a second end at the bearing side. In addition, the VTG turbocharger may further comprise a face seal assembly including a cup spring and a composite ring seal circumscribing the APS at the pressure side, with the cup spring forming a face seal with the first end of the bushing. The face seal assembly may further include a spring circumscribing the APS at the bearing side and engaging the second end of the bushing.

Turbine assemblies and related turbocharger systems having direct turbine interfaces are provided. One exemplary turbine assembly includes a first turbine housing having an outlet portion defining a fluid outlet of a first turbine and a second turbine housing having an inlet portion defining a fluid inlet of a second turbine, wherein at least a portion of the outlet portion radially surrounds at least a portion of the inlet portion to provide a direct interface from the fluid outlet of the first turbine to the fluid inlet of the second turbine in an axial direction.

Turbine assemblies and related turbocharger systems having direct turbine interfaces are provided. One exemplary turbine assembly includes a first turbine housing having an outlet portion defining a fluid outlet of a first turbine and a second turbine housing having an inlet portion defining a fluid inlet of a second turbine, wherein at least a portion of the inlet portion radially surrounds at least a portion of the outlet portion to provide a direct interface from the fluid outlet of the first turbine to the fluid inlet of the second turbine in an axial direction.

The invention relates to a turbine engine separate flow mixer centered on a longitudinal axis, comprising an exhaust housing, a shroud directly connected to the exhaust housing and intended to mix the flows originating in the turbine engine, said shroud comprising a metal sheet formed by a succession of first and second longitudinal strips distributed circumferentially around the longitudinal axis of the mixer by circumferentially placing the second strips on either side of the first strips, the first and second strips being configured to form the shroud when at rest and grooves in the shroud when operating, the grooves being defined by an alternation of internal lobes and of external lobes.

A tapered land thrust bearing device with a land surface having a substantially reduced area without changing the contour shape of the land surface even if the area of the land surface is small, and high mechanical efficiency, as well as a turbocharger provided with the bearing device. A tapered land thrust bearing device includes: a flange portion fitted onto a rotary shaft and including a first thrust portion; and a thrust member including a second thrust portion which is disposed around a through hole and which faces the first thrust portion of the flange portion.