Abstract: A turbine engine assembly includes a turbine engine case, a gearbox and a plurality of gearbox mounts that connect the gearbox to the case. The case extends along an axis between an upstream end and a downstream end. The gearbox mounts include an axial mount that extends axially in an upstream direction from the gearbox to the case.

Abstract: An assembly including a front panel is separated from a back panel by a panel fold line. Side flaps are disposed at opposing edges of the front panel and are each separated from the front panel by a flap fold line. The side flaps include a front flap surface with an adhesive material and a back flap surface opposite the front flap surface. The assembly is foldable about the panel fold line to dispose the back panel adjacent the front panel and foldable about the flap fold line to dispose the back flap surface adjacent a front surface of the back panel when the back panel is folded. In a folded position, the assembly forms a pocket between the front and back panels, and is adherable by the adhesive material to a separate surface.

Abstract: A face seal assembly for a gas turbine engine includes an engine static structure. A guide assembly supports a face seal for movement relative to the engine static structure in an axial direction. The guide assembly includes a guide pin having a first end that supports a washer that is retained by a circlip secured to the first end. The circlip is configured to limit movement of the face seal in the axial direction.

Abstract: A seal assembly includes a seal support, a spring carrier, a plurality of springs, and a seal carrier. The spring carrier is connected to the seal support by a guide assembly. The plurality of springs are disposed between the seal support and the spring carrier. The seal carrier is connected to the spring carrier and is removable therefrom.

Abstract: A gas turbine engine includes a jumper tube that extends through a first passage and a second passge.

Abstract: In one aspect, the present invention relates to a system for abrasion of optical fibers. The system includes an adjustment member, a platform disposed on the adjustment member, and a focus block disposed on the platform. A laser is disposed above, and is in optical alignment with, the focus block. The laser abrades an optical fiber positioned on the focus block.

Abstract: A method for distributing liquid in a gas turbine engine is disclosed. The method includes rotating a fan shaft coupled to a spool via a fan drive gear system. The spool drives rotation of the fan shaft through the fan drive gear system during operation of the gas turbine engine. A pump is driven via the fan shaft. Liquid is supplied from a sump to the pump under a first operating condition. Liquid is supplied from an auxiliary reservoir to the pump under a second operating condition. Liquid is pumped to a damper.

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 gas turbine engine includes a fan, a fan drive gear system coupled to drive the fan, a compressor section including a first compressor and a second compressor and a turbine section. The turbine section includes a first turbine coupled to drive a first spool, which is coupled at a first axial position to a compressor hub that is coupled to drive the first compressor. The first spool is also coupled at a second axial position to a fan drive input shaft that is coupled to drive the fan drive gear system. A second turbine is coupled through a second spool to drive the second compressor. A speed sensor probe is operable to determine a rotational speed of the first spool. The speed sensor probe is located axially aft of the first axial position and the second axial position.

Abstract: A axial face seal assembly includes first and second structures rotatable relative to one another about an axis. A carrier supports a seal that engages the second structure. The carrier is configured to move along the axis. First and second springs operatively are arranged between the first structure and the carrier. The first and second springs are configured to bias the carrier relative to the second structure respectively in first and second directions along the axis for providing a desired closing force on the second structure. A method of sealing a rotating structure includes biasing a seal toward a rotating sealing surface with a first spring to provide a desired axial closing force. The axial position of the seal relative to the rotating sealing surface is changed to an undesired axial closing force. The seal is biased with a second spring to achieve the desired axial closing force.

Abstract: A method for servicing a gas turbine engine includes providing access from a forward section of the gas turbine engine to a gearbox contained within a bearing compartment. A gas turbine is also disclosed in which a bearing package is mounted to a front center body support and a low spool. A front wall is removable from the front center body support to provide access to the gearbox.

Abstract: A bearing support assembly for supporting a bearing assembly within a bearing compartment of a gas turbine engine includes a centering spring and a bearing support member integrally joined together to form a one piece structure. The centering spring connects to the bearing assembly and has a portion that extends conically relative to a centerline axis of the gas turbine engine. The bearing support member extends from the centering spring to connect to an engine case of the gas turbine engine.

Abstract: A method for servicing a gas turbine engine includes providing access from a forward section of the gas turbine engine to a gearbox contained within a bearing compartment.

Abstract: A front center body support for a gas turbine engine includes a front center body section, a bearing section and a frustro-conical interface section, the frustro-conical interface section between the front center body section and the bearing section.

Abstract: A method for servicing a gas turbine engine includes providing access from a forward section of the gas turbine engine to a gearbox contained within a bearing compartment.

Abstract: An oil scavenge system includes a scavenge pipe which extends forward into a relatively long and narrow compartment area of a rear bearing compartment of a gas turbine engine with aggressive core size constraints. The scavenger pipe communicates collected oil to a scavenger pump to return oil to the oil sump and evacuate the oil before flooding of the seals may occur.

Abstract: An assembly including a front panel is separated from a back panel by a panel fold line. Side flaps are disposed at opposing edges of the front panel and are each separated from the front panel by a flap fold line. The side flaps include a front flap surface with an adhesive material and a back flap surface opposite the front flap surface. The assembly is foldable about the panel fold line to dispose the back panel adjacent the front panel and foldable about the flap fold line to dispose the back flap surface adjacent a front surface of the back panel when the back panel is folded. In a folded position, the assembly forms a pocket between the front and back panels, and is adherable by the adhesive material to a separate surface.

Abstract: An example method of accessing a valve assembly of a turbomachine includes accessing a check valve of the valve assembly from a first position that is radially outside a flow path through the turbomachine. The method accessing a shut off valve of the valve assembly from a second position that is radially outside the flow path. The check valve and the shut off valve are configured to influence communication of lubricant along a lubricant communication path that extends between a location radially outboard the flow path and a location radially inboard the flow path. The first position is the same as the second position in some examples.

Abstract: A gas turbine engine includes a bearing and a bearing support having a second wall extending between first and second ends and operatively supported by the bearing at a first end. An engine case is secured to the second end radially outward of the first end. A second wall integral with and extending transversely from the first wall provides a flexible support. The second wall has a flange, and a gear train component is secured to the flange. A gas turbine engine includes a support structure which supports the main rotatable structure via bearings and gear train components. The support provides both the necessary structural support for the rotor structure as well as desired flexibility for a fan drive gear system.

Abstract: A liftoff carbon seal assembly includes a rotating seal plate adjacent to a rotating seal backer plate and a rotating seal plate retainer. The rotating seal plate defines a rotating seal plate face which extends beyond a rotating seal plate retainer face of the rotating seal plate retainer with a static carbon seal is adjacent to the rotating seal plate.