Abstract: A fan drive gear system for a gas turbine engine includes a carrier that supports circumferentially arranged gears. A torque frame has circumferentially arranged fingers with each finger including a bore having a bore axis. A bushing is arranged in each bore and provides an aperture. At least one bushing has a bushing axis offset from the bore axis. A pin is disposed in the aperture and secures the carrier to the torque frame.

Abstract: A gas turbine engine includes a fan section. A turbine section is coupled to the fan section via a geared architecture. The geared architecture includes a torque frame and a flex support spaced apart from one another at a location. A gear train is supported by the torque frame. A damper is provided between the torque frame and the flex support at the location.

Abstract: A support assembly for a geared architecture includes an engine static structure. A flex support is secured to the engine static structure and includes a bellow. A support structure is operatively secured to the flex support. A geared architecture is mounted to the support structure. First members are removably secured to one of the engine static structure and the flex support and second members are removably secured to the support structure. The first and second members are circumferentially aligned with one another and spaced apart from one another during a normal operating condition. The first and second members are configured to be engageable with one another during an extreme event to limit axial movement of the geared architecture relative to the engine static structure.

Abstract: A fluid distribution system for use in a gas turbine engine includes a fan shaft, a damper, a bearing, and a pump. The damper supports the bearing, and the bearing supports the fan shaft. The pump is connected to and driven by the fan shaft. The pump is also fluidically connected to the damper.

Abstract: A turbine engine shaft includes a first sub-shaft, a second sub-shaft and a tie shaft. A first bearing surface of the first sub-shaft axially engages a second bearing surface of the second sub-shaft. The tie shaft includes an intermediate tie shaft segment connected axially between a first tie shaft segment and a second tie shaft segment. The first tie shaft segment includes a first threaded tie shaft surface that is mated with a first threaded shaft surface of the first sub-shaft. The second tie shaft segment includes a second threaded tie shaft surface that is mated with a second threaded shaft surface of the second sub-shaft. The tie shaft also includes a sub-shaft bumper stop extending radially from the intermediate tie shaft segment to a bumper stop distal end, which has a radius that is greater than a radius the first and/or second threaded shaft surfaces.

Abstract: A tie bolt for joining two parts together has a shaft. The shaft in turn has a primary thread for engaging a first part and a secondary thread for engaging a second part, wherein the primary thread and the secondary thread have different pitches. The tie bolt may be used to join together any two parts which are to be locked together to transmit torque.

Abstract: A lubrication system for a bearing assembly includes a fan shaft with a plurality of conduits, a first bearing rotatably supporting the fan shaft, and a second bearing rotatably supporting the fan shaft where the second bearing is axially spaced from the first bearing. The plurality of conduits includes at least a first conduit aligned with the first bearing and a second conduit aligned with the second bearing. A spray bar includes a plurality of supply orifices that direct lubricating fluid to the first and second bearings via at least the first and second conduits.

Abstract: A fluid distribution system for use in a gas turbine engine includes a fan shaft, a damper, a bearing, and a pump. The damper supports the bearing, and the bearing supports the fan shaft. The pump is connected to and driven by the fan shaft. The pump is also fluidically connected to the damper.

Abstract: A retention system for a fan in a gas turbine engine includes a shaft that is rotatable relative to a bearing support structure about an axis. The retention system includes fore and aft bearings that rotatably support the shaft, with the fore and aft bearings being spaced apart from each other in a direction along the axis. A machined spring reacts between the bearing support structure and the fore bearing to provide a desired axial preload.

Abstract: A lubrication system for a bearing assembly includes a fan shaft with a plurality of conduits, a first bearing rotatably supporting the fan shaft, and a second bearing rotatably supporting the fan shaft where the second bearing is axially spaced from the first bearing. The plurality of conduits includes at least a first conduit aligned with the first bearing and a second conduit aligned with the second bearing. A spray bar includes a plurality of supply orifices that direct lubricating fluid to the first and second bearings via at least the first and second conduits.

Abstract: A bearing support for a rotor of an aircraft turbine engine includes a frangible linkage designed to enable the engine to safely shut down despite the introduction of an excessive unbalance to the fan stage.