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 bi-directional auxiliary lubrication system which allows lubricant to be supplied to moving engine components after a loss of lubricant pressure from a main lubricant tank is disclosed. In a gas turbine engine, the lubrication system may siphon compressed air from a compressor to draw lubricant from a reserve lubricant tank and deliver that lubricant to the engine components. The same conduits used by the lubrication during normal operations are utilized in an opposite direction to provide the flow of lubricant from the reserve lubricant tank during such auxiliary or low-lubricant-pressure operations.

Abstract: The present disclosure relates generally to a guide vane assembly including a first airfoil, including a first airfoil trailing edge, a second airfoil, including a second airfoil leading edge, positioned aft the first airfoil to create a gap therebetween, and a seal assembly disposed within the gap to engage the first airfoil trailing edge and the second airfoil leading edge.

Abstract: A fixed-variable vane assembly includes a vane that has a fixed airfoil section and a variable airfoil section next to the fixed airfoil section. The variable airfoil section is pivotably mounted at an end thereof in a joint with a variable joint gap that controls a size of an airfoil gap between the fixed airfoil section and the variable airfoil section. A potting material is located in the variable joint gap. The potting material locks the variable joint gap and locks in the size of the airfoil gap.

Abstract: A vane strut positioning and securement system includes a housing including a washer aperture defined in an inner diameter thereof and a lock washer disposed within the washer aperture of the housing, the lock washer configured to lock a vane strut orientation under compression against a vane strut washer. The washer aperture is defined partially through a thickness of the housing, and the housing includes a strut post opening defined through the housing from the inner diameter to an outer diameter of the housing.

Abstract: A strut-flap vane system for a turbomachine includes a vane strut comprising an airfoil portion and a strut mount extending in a radially outward direction from the airfoil portion. The strut mount forms a hollow semi-cylinder and includes threading on an outer diameter thereof. The system includes an aft mount portion or portions defining a hollow semi-cylinder configured to form a strut cylinder with the strut mount such that the aft mount portion can be disposed in contact with the strut mount to form the strut cylinder. The strut cylinder defines a cylinder opening and the aft mount portion includes threading on an outer diameter thereof that aligns with the threading of the strut mount to allow a strut spanner nut to mesh with both the strut mount and the mount portion.

Abstract: A seal comprises a housing. A coating has at least two layers with a bond layer to be positioned between a housing and a second hard layer. The second hard layer is formed to be harder than the bond layer. The bond layer has a bond strength greater than or equal to 200 psi and less than or equal to 2000 psi. A gas turbine engine, and a method of forming a coating layer are also disclosed.

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

Abstract: Disclosed is a gas turbine engine including a plurality of inlet guide vanes. The gas turbine engine further includes an inlet case supporting each of the plurality of inlet guide vanes, and the inlet case is provided with at least one passageway in communication with a source of fluid. The at least one passageway is configured to communicate the fluid to each of the plurality of inlet guide vanes.

Abstract: The present disclosure relates generally to a guide vane assembly including a first airfoil, including a first airfoil trailing edge, a second airfoil, including a second airfoil leading edge, positioned aft the first airfoil to create a gap therebetween, and a seal assembly disposed within the gap to engage the first airfoil trailing edge and the second airfoil leading edge.

Abstract: One embodiment of the seal housing for a face seal described herein include a base with a seal element support and a shroud both extending from the base in a common direction. The seal element support and the base define a space for receiving a seal element. The shroud includes a tip having a head portion that tapers toward a neck portion that is reduced in size relative to the head portion. The tip is secured to a stem of the shroud through a set of circumferentially distributed countersunk holes.

Abstract: Disclosed is a gas turbine engine including a compressor section in communication with a bleed flow path. A rotary valve is provided in communication with the bleed flow path to selectively regulate a flow of fluid within the bleed flow path.

Abstract: One embodiment of the seal housing for a face seal described herein include a base with a seal element support and a shroud both extending from the base in a common direction. The seal element support and the base define a space for receiving a seal element. The shroud includes a tip having a head portion that tapers toward a neck portion that is reduced in size relative to the head portion. The tip is secured to a stem of the shroud through a set of circumferentially distributed countersunk holes.

Abstract: One embodiment of the face seal described herein includes a seal seat and a seal element carried by a seal housing. The seal element cooperates with the seal seat to establish a seal. The housing includes a seal element support and a shroud. The shroud includes a stem and a tip, and the tip is an insert secured to the stem.

Abstract: One embodiment of the face seal described herein includes a seal seat and a seal element carried by a seal housing. The seal element cooperates with the seal seat to establish a seal. The housing includes a seal element support and a shroud. The shroud includes a stem and a tip, and the tip is an insert secured to the stem.

Abstract: One embodiment of the face seal described herein includes a seal seat and a seal element carried by a seal housing. The seal element cooperates with the seal seat to establish a seal. The housing includes a seal element support and a shroud. The seal housing is made of a parent material and the shroud has a tip impregnated with a second material.

Abstract: An exemplary valve device for controlling flow of a turbomachine fluid includes a housing and a flow control assembly within the housing. The housing has a first inlet, a second inlet, and an outlet. Movement of the housing to a first orientation causes the flow control assembly to move to a first position to restrict flow of a turbomachine fluid into the housing through the second inlet. Movement of the housing to a second orientation causes the flow control assembly to move to a second position to restrict flow of the turbomachine fluid into the housing through the first inlet.

Abstract: A turbofan engine comprises an engine case. A gaspath extends through the engine case. A fan has a circumferential array of fan blades. A fan case encircles the fan blades radially outboard of the engine case. A plurality of fan case vanes extend aftward and outward from the engine case to the fan case. A forward frame comprises a plurality of vanes radially across the gaspath. A torque box couples the fan case vanes to the forward frame. A transmission couples a shaft to a fan shaft to drive the fan. A fan bearing assembly couples a stationary forward hub structure to the fan shaft.

Abstract: An assembly includes a gas turbine engine, a compartment wall, and a gutter system. The gas turbine engine has a spool connected to a fan shaft via a gear system. The compartment wall is positioned radially outward from the gear system. The gutter system is positioned radially outward from the gear system for capturing lubricating liquid slung from the gear system and positioned radially inward of the compartment wall. The gutter system includes a gutter and a flow passage fluidically connected to the gutter. The flow passage has a plurality of holes that allow the lubricating liquid to pass through the flow passage into a space between the flow passage and the compartment wall.

Abstract: A turbofan engine comprises an engine case. A gaspath extends through the engine case. A fan has a circumferential array of fan blades. A fan case encircles the fan blades radially outboard of the engine case. A plurality of fan case vanes extend outward from the engine case to the fan case. A front frame assembly includes a plurality of vanes extending radially across the gaspath. A transmission couples a shaft to a fan shaft to drive the fan. A bearing assembly couples the shaft to the front frame assembly. A bearing support extends aftward and radially inward from the front frame assembly to the bearing assembly.