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 turbocharger includes: a shaft connecting a compressor wheel and a turbine wheel; a thrust collar rotating together with the shaft; a thrust bearing holding the thrust collar for rotation; and a bearing housing holding the thrust bearing, wherein the bearing housing includes: an oil supply passage for supplying oil for lubrication to the thrust bearing; an oil discharge passage from which the oil supplied to the thrust bearing is discharged; a wall portion facing the thrust collar; and a groove portion formed in the wall portion and extending from the thrust collar toward a discharge port of the oil discharge passage.

A high temperature flange joint in a gas turbine engine includes a first flange formed on a first component abutting a second flange formed on a second component. The flange joint includes multiple adjacently spaced bolt connections. Each bolt connection includes a first spacer plate bearing against the first flange and a second spacer plate bearing against the second flange. First and second lock washers are provided that bear against the first and second spacer plates respectively. A bolt is inserted through the first and second flanges, the first and second spacer plates and the first and second lock washers. The bolt is preloaded to clamp the first flange to the second flange. Each spacer plate has a respective thickness and is sized to enhance a bearing surface in contact with the respective flange. Thereby, a bolt preload is maintained during operation of the gas turbine engine.

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 propulsor section including a propulsor supported on a propulsor shaft, a turbine section including a turbine shaft, a compressor section, and an epicyclic gear train interconnecting the propulsor shaft and the turbine shaft. The 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. The first and second portions have grooves at the radial interface that form a hole that expels oil through the ring gear.

In accordance with one aspect of the present disclosure, a turbocharger having a rolling element bearing (REB) assembly contained within a bearing housing includes an axial damper configured to dampen and limit axial displacement of the REB assembly. The axial damper can include different embodiments, including an elastomeric axial damper, wire mesh, or oil film, for interrupting contact between the bearing assembly and a displacement limit when an axial displacement force exceeds a preload force. Further, the axial damper can include an apparatus having at least two axially compressible rings, where one of the axially compressible rings includes a displacement limit feature.

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 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.

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.

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).