A gas turbine engine according to an example of the present disclosure includes, among other things, a turbo fan shaft and a turbo fan supported on the fan shaft, a compressor section having compressor hubs with blades driven about an axis, and an epicyclic gear system driving the fan shaft. The gear system includes a carrier supporting intermediate gears that mesh with a sun gear, a ring gear surrounding and meshing with the intermediate gears, the ring gear including first and second portions each having an inner periphery with teeth, the first and second portions abutting one another at a radial interface, each of the first and second portions including a flange extending radially outward, and the first and second portions having grooves at the radial interface which form a hole that expels oil through the ring gear to a gutter, and an input shaft driving the fan shaft through the gear system, the input shaft connected to the sun gear.

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, and 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.

An epicyclic gear train includes a carrier that supports star gears that mesh with a sun gear. A ring gear surrounds and meshes with the star gears. The star gears are supported on respective journal bearings. Each of the journal bearings includes a peripheral journal surface and each of the star gears includes a radially inner journal surface that is in contact with the peripheral journal surface of the respective journal bearing.

A turbine rotor includes a rotor body and a balancing weight slot defined in an exterior circumference of the body. The balancing weight slot has a first axial width and a first radially outward facing surface at a first radial distance from a rotor axis. The rotor also includes a balancing weight entry port defined in a portion of the exterior circumference of the rotor body and aligned with the balancing weight slot. The balancing weight entry port has a second axial width greater than the first axial width and a second radially outward facing surface at a second radial distance from the axis of the rotor body that is smaller than the first radial distance. A method may include machining the entry port into the rotor with a tool. The method may be applied to a new rotor, or to remove cracks initiating from a previous entry port.

An epicyclic gear train for a turbine engine includes a gutter with an annular channel. A rotating structure includes a ring gear. The rotating structure 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 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 geared architecture for a gas turbine engine comprises a fan shaft and a fan supported on the fan shaft and defining a bypass flow ratio greater than about six. A frame supports the fan shaft. A gear system drives the fan shaft. The gear system has a gear reduction ratio of greater than or equal to about 2.3. A torque frame at least partially supports the gear system. An input is coupled to the gear system. A downstream turbine is coupled to rotatably drive the input coupling. The downstream turbine defines a pressure ratio that is greater than about five (5).

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 having a plurality of compressor hubs with blades driven by the turbine shaft about an engine axis, 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 and a ring gear including first and second portions. The first and second portions have axially opposed faces abutting one another at a radial interface.

In one exemplary embodiment, a gas turbine engine includes a bypass flow ratio greater than about ten. A fan supported on a fan shaft having a plurality of fan blades and a low fan pressure ratio of less than 1.45 measured across the fan blades alone. A gutter with an annular channel. A gear system connected to the fan shaft having a gear reduction ratio greater than 2.5, planetary gears, and a ring gear with an aperture that is axially aligned with the annular channel. A torque frame at least partially supports the gear system. A low pressure turbine with an inlet, an outlet, and a low pressure turbine pressure ratio greater than 5:1.

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 gear train for a turbine engine includes a gutter with an annular channel. A rotating structure includes a ring gear. The rotating structure 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 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.