Abstract: A gas turbine engine includes a fan located at a forward portion of the gas turbine engine, and a compressor section and a turbine section arranged in serial flow order. The compressor section and the turbine section together define a core airflow path. A rotary member is rotatable with the fan and with a low pressure turbine of the turbine section. The low pressure turbine includes a rotating drum to which a first airfoil structure is connected and extends radially inward toward the rotary member. A torque frame connects the rotating drum to the rotary member and transfers torque from the first airfoil structure mounted to the rotating drum to the rotary member. The torque frame includes an inner disk mounted to the rotary member, an outer ring and a second airfoil structure formed separately from the outer ring and connected thereto by a releasable connecting structure. The second airfoil structure extends radially inward from the outer ring toward the inner disk.

Abstract: An unducted single fan engine includes a housing having one or more fan blades coupled to the housing and configured to rotate circumferentially. The engine has one or more outlet guide vanes coupled to the housing. Each of the one or more guide vanes has a leading edge portion having a variable leading edge. The engine has one or more actuation devices coupled to each of the one or more outlet guide vanes. The one or more actuation devices are configured to control the variable leading edge of the respective outlet guide vane. The variable leading edge is controllable to vary the pitch, camber, lean angle, or sweep of the respective outlet guide vane.

Abstract: An unducted single fan engine includes a housing having one or more fan blades coupled to the housing and configured to rotate circumferentially. The engine has one or more outlet guide vanes coupled to the housing. Each of the one or more guide vanes has a leading edge portion having a variable leading edge. The engine has one or more actuation devices coupled to each of the one or more outlet guide vanes. The one or more actuation devices are configured to control the variable leading edge of the respective outlet guide vane. The variable leading edge is controllable to vary the pitch, camber, lean angle, or sweep of the respective outlet guide vane.

Abstract: A passive clearance control limits thermal expansion between stator components relative to rotor components. A control ring controls clearance in a passive manner and is located on or adjacent to stationary components which thermally expand during engine operation. The control ring is formed of material having low coefficient of thermal expansion such as CMCs (Ceramic Matrix Composites) and therefore limits, inhibits or restrains expansion of the adjacent stator components as temperatures increase. Limiting expansion of the stator component reduces rotor/stator clearances and limits parasitic leakage of fluid along the flow path through the engine core.

Abstract: A passive clearance control limits thermal expansion between stator components relative to rotor components. A control ring controls clearance in a passive manner and is located on or adjacent to stationary components which thermally expand during engine operation. The control ring is formed of material having low coefficient of thermal expansion such as CMCs (Ceramic Matrix Composites) and therefore limits, inhibits or restrains expansion of the adjacent stator components as temperatures increase. Limiting expansion of the stator component reduces rotor/stator clearances and limits parasitic leakage of fluid along the flowpath through the engine core.

Abstract: A passive clearance control limits thermal expansion between stator components relative to rotor components. A control ring controls clearance in a passive manner and is located on or adjacent to stationary components which thermally expand during engine operation. The control ring is formed of material having low coefficient of thermal expansion such as CMCs (Ceramic Matrix Composites) and therefore limits, inhibits or restrains expansion of the adjacent stator components as temperatures increase. Limiting expansion of the stator component reduces rotor/stator clearances and limits parasitic leakage of fluid along the flowpath through the engine core.

Abstract: A passive clearance control limits thermal expansion between stator components relative to rotor components. A control ring controls clearance in a passive manner and is located on or adjacent to stationary components which thermally expand during engine operation. The control ring is formed of material having low coefficient of thermal expansion such as CMCs (Ceramic Matrix Composites) and therefore limits, inhibits or restrains expansion of the adjacent stator components as temperatures increase. Limiting expansion of the stator component reduces rotor/stator clearances and limits parasitic leakage of fluid along the flowpath through the engine core.

Abstract: A method for assembling a gas turbine engine includes providing a core gas turbine engine including a high-pressure compressor, a combustor, and a turbine, and coupling a counter-rotating fan assembly to the core gas turbine engine such that air discharged from the counter-rotating fan assembly is channeled directly into an inlet of the gas turbine engine compressor.

Abstract: A method for assembling a turbine engine to facilitate preventing ice accumulation on the turbine engine during engine operation. The method includes coupling a manifold to the gas turbine engine such that the manifold is coupled in thermal communication with a heat source, coupling a first heat pipe to the manifold such that the first heat pipe partially circumscribes the gas turbine engine in a clockwise orientation, and coupling a second heat pipe to the manifold such that the second heat pipe partially circumscribes the gas turbine engine in a counter-clockwise orientation.

Abstract: A method for assembling a gas turbine engine includes coupling a high-pressure compressor to a high-pressure turbine using a first shaft, coupling a fan assembly to a low-pressure turbine using a second shaft, and coupling a differential squeeze film damper assembly between the first and second shafts.

Abstract: A Turbofan engine includes a fan mounted to a fan frame inside a fan nacelle. A booster compressor is joined to the fan inboard a flow splitter.

Abstract: A method for assembling a gas turbine engine includes providing a core gas turbine engine including a high-pressure compressor, a combustor, and a turbine, coupling a counter-rotating fan assembly to the core gas turbine engine such that air discharged from the counter-rotating fan assembly is channeled directly into an inlet of the gas turbine engine compressor, and coupling a counter-rotating low-pressure turbine assembly to the counter-rotating fan assembly.

Abstract: A method for assembling a gas turbine engine includes coupling a low-pressure turbine to a core turbine engine, and coupling a counter-rotating fan assembly including a first fan assembly and a second fan assembly to the low-pressure turbine such that the first fan assembly rotates in a first direction and the second fan assembly rotates in an opposite second direction.

Abstract: A method facilitates assembling a gas turbine engine. The method comprises coupling a low-pressure turbine rotatable about a drive shaft to a counter-rotating fan assembly including a first fan assembly and a second fan assembly wherein the first fan assembly rotates in a first direction and the second fan assembly rotates in an opposite second direction. The method also comprises coupling a planetary gearbox substantially circumferentially about the drive shaft such that an input of the gearbox is coupled to the low-pressure turbine and an output of the gearbox is coupled to the counter-rotating fan assembly, and such that the gearbox is positioned within a lubrication fluid sump that substantially circumscribes the gearbox.

Abstract: A method for assembling a gas turbine engine includes coupling a low-pressure turbine to a core turbine engine, coupling a gearbox to the low-pressure turbine, coupling a first fan assembly to the gearbox such that the first fan assembly rotates in a first direction, and coupling a mechanical fuse between the first fan assembly and the low-pressure turbine such that the mechanical fuse fails at a predetermined moment load.

Abstract: A method for assembling a gas turbine engine includes coupling a low-pressure turbine to a core turbine engine, coupling a counter-rotating fan assembly including a forward fan assembly and an axially aft fan assembly to the low-pressure turbine such that the forward fan assembly rotates in a first direction and the aft fan assembly rotates in an opposite second direction, and coupling a booster compressor to the low-pressure turbine such that the booster compressor rotates in the first direction.

Abstract: A method for assembling a gas turbine engine including providing a core gas turbine engine at least partially defined by a frame. The gas turbine engine has a drive shaft that is rotatable about a longitudinal axis of the core gas turbine engine. A counter-rotating fan assembly is coupled to the low-pressure turbine. The counter-rotating fan includes a first fan assembly that rotates in a first direction and a second fan assembly that rotates in an opposite second direction. A booster compressor is coupled to the second fan assembly. A first bearing assembly is mounted between the drive shaft and the frame and operatively coupled to the first fan assembly to transmit thrust force from the first fan assembly to the frame. A second bearing assembly is mounted with respect to the second fan assembly and operatively coupled to the second fan assembly to transfer thrust force from at least one of the second fan assembly and the booster compressor to the second bearing assembly.

Abstract: A gearbox includes a support structure, at least one sun gear coupled within the support structure, and a plurality of planetary gears coupled within the support structure. The support structure includes a first portion, an axially aft second portion, and a thrust spring coupled between the first and second portions.

Abstract: A method for assembling a gas turbine engine includes coupling a low-pressure turbine to a core turbine engine, coupling a gearbox including an input, a first output, and a second output, to the low-pressure turbine, coupling a first fan assembly to the gearbox first output, and coupling a second fan assembly to the gearbox second output.