Abstract: A gas turbine engine may include propulsor means for providing propulsion, first and second compression means, reduction means for reducing a rotational speed of an output that drives the propulsor means relative to an input, and first and second expansion means. The propulsor means may include a propulsor rotor and at least one propulsor blade. The first compression means may include an entrance at a splitter, and the at least one propulsor blade may be forward of the splitter relative to an engine longitudinal axis. The reduction means may interconnect the second expansion means with the first compression means and the propulsor rotor. The first compression means may include a first compressor rotor that may be rotatable together with the propulsor rotor at a common speed with the output of the reduction means.

Abstract: A gas turbine engine may include propulsor means for providing propulsion, first compression means for compressing airflow from the propulsor means, second compression means for compressing airflow from the first compression means, reduction means for reducing a rotational speed of an output that drives the propulsor means relative to an input, first expansion means for driving the second compression means in response to expanding airflow from the second compression means, and second expansion means for driving the input of the reduction means in response to expanding airflow from the first expansion means. The reduction means may be straddle mounted by a first bearing forward of the reduction means and a second bearing aft of the reduction means relative to an engine longitudinal axis.

Abstract: A fan drive gear system for a turbine engine includes a gear system with a plurality of compound intermediate gears that each include a first gear portion and a second gear portion. The second gear portion includes a forward gear portion and an aft gear portion, and a ring gear assembly includes a forward ring gear that is engaged to the forward gear portion and an aft ring gear that is engaged to the aft gear portion. A carrier supports rotation of the plurality of intermediate gears with a plurality of corresponding journal bearing assemblies.

Abstract: A method of mounting a gear train to a torque frame comprises the steps of providing a unitary carrier having a central axis that includes spaced apart side walls and circumferentially spaced connecting structure defining mounts that interconnect the side walls, spaced apart apertures provided between the mounts at an outer circumference of the carrier, gear pockets provided between the side walls and the mounts extending to the apertures, and a central opening in at least one of the side walls. A plurality of intermediate gears are inserted in the carrier. A first ring gear half of a ring gear is placed about the outer periphery of the intermediate gears. A torque frame is attached to the carrier.

Abstract: A gas turbine engine includes a plurality of blades that deliver air into a compressor section and a drive gear system including an epicyclic transmission. A drive shaft interconnects a gear carrier of the epicyclic transmission and the plurality of blades. A turbine section drives an input of the drive gear system through a turbine shaft. The drive gear system is straddle mounted by a first bearing forward of the drive gear system and a second bearing aft of the drive gear system. A ring gear of the epicyclic transmission is coupled to an engine case with a compliant flexure at a position between the first bearing and the second bearing.

Abstract: A gas turbine engine has a fan drive turbine driving a gear reduction, the gear reduction, in turn, driving a fan rotor, the fan rotor delivering air into a bypass duct as bypass air and into a compressor section as core flow. A forward bearing is positioned between the gear reduction and the fan rotor and supports the gear reduction. A second bearing is positioned aft of the gear reduction and supports the gear reduction. The second bearing is a thrust bearing. A fan drive turbine drive shaft drives the gear reduction. The fan drive turbine drive shaft has a weakened link which is aft of the second bearing such that the fan drive turbine drive shaft will tend to fail at the weakened link, and at a location aft of the second bearing.

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a propulsor, a compressor section, a turbine section and an epicyclic gear system. The turbine section includes a first turbine and a second turbine. The second turbine drives the propulsor through the epicyclic gear system. The epicyclic gear system includes a carrier. A drive shaft interconnects the carrier and the propulsor. A frame supports at least a portion of the drive shaft. A flexible support at least partially supports the gear system relative to an engine static structure.

Abstract: A fan drive gear system for a turbine engine includes a gear system with a plurality of compound intermediate gears that each include a first gear portion and a second gear portion. The second gear portion includes a forward gear portion and an aft gear portion and a ring gear assembly includes a forward ring gear that is engaged to the forward gear portion and an aft ring gear that is engaged to the aft gear portion. A carrier supports rotation of the plurality of intermediate gears with a plurality of corresponding journal bearing assemblies.

Abstract: A gas turbine engine includes a fan shaft diving a fan having fan blades. The gas turbine engine also includes a gear system including a sun gear surrounded by a plurality of intermediate gear, a carrier at least partially supporting said plurality of intermediate gears, and a ring gear surrounding said plurality of intermediate gears, wherein said sun gear is driven by a turbine. The gas turbine engine also includes a flexible coupling fixing said ring gear from rotation relative to an engine static structure and a lubricating system for said gear system. Said lubricating system includes a lubricant input, there being a stationary first bearing receiving lubricant from said lubricant input. Said bearing has an inner first race in which lubricant flows, and a second bearing for rotation within said first bearing. Said second bearing has a first opening in registration with said inner first race such that lubricant may flow from said inner first race through said first opening into a first conduit.

Abstract: A fan drive gear system for a turbofan engine according to an exemplary embodiment of this disclosure, among other possible things includes a sun gear that is rotatable about an axis, a plurality of intermediate gears driven by the sun gear, and a baffle that is disposed between at least two of the plurality of intermediate gears for defining a lubricant flow path from an interface between the sun gear and at least one of the plurality of intermediate gears. The baffle includes a channel with at least one ramp portion directing lubricant.

Abstract: A gas turbine engine according to an example of the present disclosure includes 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.

Abstract: A gas turbine engine has a fan drive turbine driving a gear reduction, the gear reduction, in turn, driving a fan rotor, the fan rotor delivering air into a bypass duct as bypass air and into a compressor section as core flow. A forward bearing is positioned between the gear reduction and the fan rotor and supports the gear reduction. A second bearing is positioned aft of the gear reduction and supports the gear reduction. The second bearing is a thrust bearing. A fan drive turbine drive shaft drives the gear reduction. The fan drive turbine drive shaft has a weakened link which is aft of the second bearing such that the fan drive turbine drive shaft will tend to fail at the weakened link, and at a location aft of the second bearing.

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, propulsor means, first compression means, second compression means, reduction means for reducing a rotational speed of an output that drives the propulsor means relative to an input, first expansion means, and second expansion means. The reduction means includes an epicyclic gear system with a gear reduction. The gear system is straddle-mounted by first and second bearings on opposite sides of the gear reduction relative to an engine longitudinal axis.

Abstract: A gas turbine engine includes a propulsor that has propulsor blades, a propulsor shaft for driving the propulsor, a propulsor shaft support that supports said propulsor shaft, said propulsor shaft support defining a propulsor shaft support transverse stiffness, a gear system connected to said propulsor shaft, said gear system includes a gear mesh defining a gear mesh transverse stiffness, and a flexible support which supports said gear system relative to a static structure and defines a flexible support transverse stiffness, wherein said flexible support transverse stiffness is less than 11% of said propulsor shaft support transverse stiffness and said flexible support transverse stiffness is less than 8% of said gear mesh transverse stiffness.

Abstract: A fan drive gear system for a turbofan engine according to an exemplary embodiment of this disclosure, among other possible things includes a sun gear that is rotatable about an axis, a plurality of intermediate gears driven by the sun gear, and a baffle that is disposed between at least two of the plurality of intermediate gears for defining a lubricant flow path from an interface between the sun gear and at least one of the plurality of intermediate gears. The baffle includes a channel with at least one ramp portion directing lubricant.

Abstract: A fan drive gear system for a turbine engine includes an auxiliary reservoir that is disposed radially outward of a rotating carrier and an oil director that is attached to the carrier. The oil director imparts a rotational flow direction into expelled oil to drive the expelled oil tangentially against an oil receiving surface and into the auxiliary reservoir.

Abstract: A gas turbine engine includes a plurality of blades that deliver air into a compressor section and a drive gear system including an epicyclic transmission. A drive shaft interconnects a gear carrier of the epicyclic transmission and the plurality of blades. A turbine section drives an input of the drive gear system through a turbine shaft. The drive gear system is straddle mounted by a first bearing forward of the drive gear system and a second bearing aft of the drive gear system. A ring gear of the epicyclic transmission is coupled to an engine case with a compliant flexure at a position between the first bearing and the second bearing.

Abstract: An exemplary gas turbine engine includes a fan section including a fan rotor and at least one fan blade. A fan pressure ratio across the at least one fan blade is less than 1.45, noninclusive of the pressure across any fan exit guide vane system. The engine further includes a low-pressure compressor having a low-pressure compressor rotor that rotates together with the fan rotor at a common speed in operation, and a geared architecture that drives the low-pressure compressor rotor and the fan rotor. The geared architecture has a gear reduction ratio of greater than 2.5. The engine further includes a high-pressure compressor having a pressure ratio greater than 20, a low-pressure turbine having a pressure ratio greater than 5, and a bypass ratio greater than 10.

Abstract: A fan drive gear system for a turbine engine includes a gear system with a plurality of compound intermediate gears that each include a first gear portion and a second gear portion. The second gear portion includes a forward gear portion and an aft gear portion and a ring gear assembly includes a forward ring gear that is engaged to the forward gear portion and an aft ring gear that is engaged to the aft gear portion. A carrier supports rotation of the plurality of intermediate gears with a plurality of corresponding journal bearing assemblies.

Abstract: A gas turbine engine according to an example of the present disclosure includes 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.