The contact seal assembly for a shaft of a gas turbine engine includes a carbon seal mounted in a fixed position within a seal housing, and an annular seal runner adapted to be connected to the shaft of the gas turbine engine and rotatable relative to the carbon ring segments. The seal runner is disposed adjacent to and radially inwardly from the carbon ring segments to form a contact interface between the seal runner and the carbon ring segments which forms a substantially fluid tight seal. The seal runner includes a coolant scoop disposed in a cavity defined by the seal housing, a first slinger disposed between the coolant scoop and the contact interface, a second slinger disposed between the first slinger and the contact interface, and a coolant collector groove disposed between the first slinger and the second slinger.

A gas turbine engine includes a bypass ratio greater than about ten (10). A fan is supported on a fan shaft and has a plurality of fan blades. A gear system is connected to the fan shaft and a plurality of planetary gears. A first set of opposed angled ring gear teeth are separated from a second set of opposed angled ring gear teeth. A lubricant flow path is located axially between the first set of opposed angled ring gear teeth and the second set of opposed angled ring gear teeth. An annular channel axially is aligned with the lubricant flow path. A low pressure turbine has an inlet, an outlet, and a low pressure turbine pressure ratio greater than 5:1. A low fan pressure ratio is less than 1.45 across the fan blade alone.

A sealing unit for a turbocharger for sealing a transition from a bearing housing into a compressor housing, and a method for producing a sealing unit of this type. The sealing unit includes a sealing bush which is designed for common rotation with a shaft of a turbocharger, a slide ring, and first and second groove rings. The first and second groove rings are designed for common rotation with the sealing bush and are arranged on the sealing bush. The slide ring is arranged between the first and second groove rings in the axial direction so that radially extending sealing gaps are formed on both sides of the slide ring between the slide ring and the respective groove ring.

In a turbocharger for receiving exhaust gas from an internal combustion engine and for delivering compressed air to the internal combustion engine, a backplate may include a lubricant stall protrusion, such as a rib, may be placed in recirculation or collection recesses of the backplate to stall recirculating lubricant flow and direct the lubricant into a bearing housing lubricant core and drain to reduce an amount of lubricant proximate piston rings and leaking into a compressor housing of the turbocharger. When an lubricant deflector is used, the lubricant stall protrusion stalls recirculating lubricant that is outboard of the lubricant deflector, and may have an outer protrusion edge closely matching the outboard contour of the lubricant deflector to minimize a flow gap there between.

A gas turbine engine includes a bypass ratio greater than about ten (10). A fan is supported on a fan shaft and has a plurality of fan blades. A gear system is connected to the fan shaft. A plurality of planetary gears and a first set of opposed angled ring gear teeth are separated from a second set of opposed angled ring gear teeth. A lubricant flow path is located axially between the first set of opposed angled ring gear teeth and the second set of opposed angled ring gear teeth. A gear system support is relative to a fixed housing facilitating segregation of vibrations. An annular channel is axially aligned with the lubricant flow path. A low pressure turbine has an inlet, an outlet, and a low pressure turbine pressure ratio greater than 5:1.

A gas turbine engine according to an example of the present disclosure includes, among other things, a fan section including a turbo fan supported on a turbo fan shaft, a turbine section including a turbine shaft, and an epicyclic gear train interconnecting the turbo fan shaft and the turbine shaft. The epicyclic gear train includes a sun gear coupled to the turbine shaft, intermediary gears arranged circumferentially about and meshing with the sun gear, a carrier supporting the intermediary gears, and a ring gear including first and second portions each having an inner periphery with teeth, the first and second portions arranged about and intermeshing with the intermediate gears, the first and second portions abutting one another at a radial interface, the first and second portions including respective flanges extending along the radial interface radially outward from the teeth, and the teeth of the first and second portions being oppositely angled teeth.

A turbine engine according to an example of the present disclosure includes, among other things, a fan shaft, at least one tapered bearing mounted on the fan shaft, the fan shaft including at least one passage extending in a direction having at least a radial component, and adjacent the at least one tapered bearing, a fan mounted for rotation on the at least one tapered bearing. An epicyclic gear train is coupled to drive the fan, the epicyclic gear train including a carrier supporting intermediate gears that mesh with a sun gear, and a ring gear surrounding and meshing with the intermediate gears, wherein the epicyclic gear train defines a gear reduction ratio of greater than or equal to 2.3. A turbine section is coupled to drive the fan through the epicyclic gear train, the turbine section having a fan drive turbine that includes a pressure ratio that is greater than 5. The fan includes a pressure ratio that is less than 1.45, and the fan has a bypass ratio of greater than ten (10).

An epicyclic gearbox assembly for a gas turbine engine includes a sun gear assembly; a planet gear assembly engaged with the sun gear assembly; and a ring gear assembly including one or more ring gears engaged with the planet gear assembly. The epicyclic gearbox assembly further includes a lubrication fluid collection assembly having a rotating oil scoop extending in a circumferential direction around the ring gear assembly, the rotating oil scoop coupled to the ring gear assembly at a location forward of one or more ring gears of the ring gear assembly.

The invention is related to the area of aviation engine building, particularly, to the elements of the gas turbine engine lubrication system. Accessory gearbox containing a gear, a branch pipe, bearings, a centrifugal impeller with blades. The centrifugal impeller with the blades contains a shell with the potential formation of inner cavities, windows for the gas-oil mixture inlet and air outlet, the blades have different lengths and are located at the angles and to the gear rotation axis. Besides, the centrifugal impeller may contain curvilinear blades. Besides, the centrifugal impeller may contain at least two oil and air separation stages installed in series. The implementation of the invention proposed with the distinctive features above, in combination with the known features enables improvement of the assembly technology, reduction of the outline dimensions and weight of the accessory gearbox, improvement of the oil separation.

An epicyclic gear train for a gas turbine engine according to an example of the present disclosure includes, among other things, a gutter having an annular channel, a sun gear rotatable about an axis, intermediary gears arranged circumferentially about and meshing with the sun gear, a carrier supporting the intermediary gears, and a ring gear arranged about and intermeshing with the intermediary gears, the ring gear having an aperture axially aligned with the annular channel. The ring gear includes axially spaced apart walls that extend radially outward to define a passageway, and the passageway is arranged radially between the aperture and the annular channel such that the walls inhibit an axial flow of an oil passing from the aperture toward the annular channel.