An epicyclic gear train for a turbine engine includes a gutter with an annular channel. A rotating structure includes a ring gear that has an aperture that is axially aligned with the annular channel. Axially spaced apart walls extend radially outward relative to the rotating structure to define a passageway. The passageway is arranged radially between and axially aligned with the aperture and the annular channel. The walls are configured to inhibit an axial flow of an oil passing from the aperture toward the annular channel.

A demister for a gearing system includes a main body having an inner annular rim coupled to an outer annular rim through a first wall and a second wall opposite from the first wall. The main body is configured to be rotated about a central longitudinal axis to create centrifugal forces that separate oil mist particles from air. First fluid passages extend radially between and through the inner annular rim and the outer annular rim. The first fluid passages include a fluid inlet opening in the outer annular rim and a fluid outlet opening in the inner annular rim. The fluid inlet opening is configured to accept incoming air. The fluid outlet opening is configured to discharge filtered air.

A gas turbine engine according to an example of the present disclosure includes, among other things, a propulsor section including a propulsor supported on a propulsor shaft, a turbine section including a turbine shaft, and an epicyclic gear train interconnecting the propulsor 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 intermeshing with the intermediate gears. The first and second portions have axially opposed faces abutting one another at a radial interface and respective flanges extending along the radial interface radially outward from the teeth. The first and second portions define a trough axially between and separating the teeth of the first portion from the teeth of the second portion. The first and second portions include facing recesses that form an internal annular cavity along the radial interface.

A demister for a gearing system includes a main body having an inner annular rim coupled to an outer annular rim through a first wall and a second wall opposite from the first wall. The main body is configured to be rotated about a central longitudinal axis to create centrifugal forces that separate oil mist particles from air. First fluid passages extend radially between and through the inner annular rim and the outer annular rim. The first fluid passages include a fluid inlet opening in the outer annular rim and a fluid outlet opening in the inner annular rim. The fluid inlet opening is configured to accept incoming air. The fluid outlet opening is configured to discharge filtered air.

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.

An assembly includes: a fan drive reducing gear of an aircraft turbine engine, and a lubrication system including: a housing enclosing the reducing gear; a device for spraying lubricant onto the reducing gear; a lubricant supply pipe intended to convey the lubricant towards the spraying device; a lubricant recovery pipe communicating with a bottom of the housing; a controlled valve equipping the recovery pipe; and a lubricant overflow discharge pipe connected to an overflow outlet of the bottom of the housing situated above a horizontal level of a bottom point of a gearing of the reducing gear, and to the recovery pipe, downstream from the valve.

A gas turbine engine according to an example of the present disclosure includes, among other things, a propulsor section including a propulsor supported on a propulsor shaft, a turbine section including a turbine shaft, and an epicyclic gear train interconnecting the propulsor 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 intermeshing with the intermediate gears. The first and second portions have axially opposed faces abutting one another at a radial interface and respective flanges extending along the radial interface radially outward from the teeth. The first and second portions define a trough axially between and separating the teeth of the first portion from the teeth of the second portion. The first and second portions include facing recesses that form an internal annular cavity along the radial interface.

A method of retrofitting a gear box assembly with an emergency lubrication system includes removing plugs from visual inspection ports of a gearbox housing, removing a breather from a breather port of the gearbox housing, and installing jet plugs into the respective visual inspection ports and breather port, wherein each jet plug includes a respective jet tube.

An assembly includes: a fan drive reducing gear of an aircraft turbine engine, and a lubrication system including: a housing enclosing the reducing gear; a device for spraying lubricant onto the reducing gear; a lubricant supply pipe intended to convey the lubricant towards the spraying device; a lubricant recovery pipe communicating with a bottom of the housing; a controlled valve equipping the recovery pipe; and a lubricant overflow discharge pipe connected to an overflow outlet of the bottom of the housing situated above a horizontal level of a bottom point of a gearing of the reducing gear, and to the recovery pipe, downstream from the valve.

The invention relates to a lubricating device for controlling lubrication in a stepped transmission comprising a splitter section (10, 20) with an input shaft (I) and a main gear section (30, 40, 50, 60) with an output shaft (O) and a countershaft (C); where the splitter section (10, 20) comprises a first splitter gear set (10) connectable to the input shaft (I) by a first gear shift mechanism (23); and a second splitter gear set (20) connectable to the input shaft (I) by the first gear shift mechanism (23); and connectable to the output shaft (O) by a second gear shift mechanism (33). A lubrication arrangement for the second splitter gear set (20) is arranged to be controlled by the current positions of the first and the second gear shift mechanisms (23, 33); wherein the lubrication arrangement is controlled to at least reduce lubrication when the first and the second gear shift mechanisms (23, 33) are simultaneously connected to or disconnected from the second splitter gear set (20).