Abstract: A hybrid electric gas turbine engine includes a fan section having a fan, a turbine section having a turbine drivably connected to the fan through a main shaft that extends along a central longitudinal axis, a gas generating core extending along a first axis that is radially offset from the central longitudinal axis, and an electric motor drivably connected to the main shaft, wherein the electric motor is colinear with the main shaft.

Abstract: A turbofan engine includes a fan rotatable about an axis, a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the combustor, a fan drive gear system including a carrier for supporting a plurality of gears, and a scupper capturing lubricant during gear operation and directing lubricant into the carrier. A fan drive gear system is also disclosed.

Abstract: A gearbox assembly for a gas turbofan engine includes a sun gear rotatable about an axis and a plurality of intermediate gears driven by the sun gear. A baffle disposed between at least two of the plurality of intermediate gears includes a first gap distance within a first gap portion and a second gap distance within a second gap portion. The first gap portion is disposed between the baffle and one of the intermediate gears away from the meshed interface with the sun gear and the second gap portion is disposed near the interface with the sun gear. The first gap distance within the first gap portion is different than the second gap distance within the second gap portion to define a desired lubricant flow path.

Abstract: A gas turbine includes a shaft, a turbine coupled with the shaft for rotation with the shaft, and a bearing coupled with the shaft to facilitate rotation of the shaft. A bearing nut is adjacent the bearing on the shaft. The turbine has a first load path and the bearing has a second load path. The bearing nut exerts a force on the bearing such that the first load path is not aligned with the second load path relative to a central axis of the gas turbine engine. A method of assembling a gas turbine engine is also disclosed.

Abstract: Hybrid electric propulsion systems are described. The hybrid electric propulsion systems include a gas turbine engine including a low speed spool and a high speed spool, the low speed spool including a low pressure compressor and a low pressure turbine, and the high speed spool including a high pressure compressor and a high pressure turbine, a mechanical power transmission configured to at least one of extract power from and supply power to at least one of the low speed spool and the high speed spool, an electric motor configured to augment rotational power of at least one of the low speed spool and the high speed spool, and a controller operable to control a power augmentation of at least one of the low speed spool and the high speed spool during an operational stress state of operation of the gas turbine engine.

Abstract: A turbofan engine includes a main engine shaft rotatable about an engine axis. A bearing assembly supports rotation of the main engine shaft. A bearing compartment defines an enclosed space around the bearing assembly. An electric machine is supported within the bearing compartment and coupled to the main engine shaft. A turbofan engine assembly and a method are also disclosed.

Abstract: An aircraft includes at least one gas turbine engine connected to a wing via an engine pylon. The gas turbine engine includes an engine core having a compressor section, a combustor section, and a turbine section and at least one actively cooled engine system. A fan is disposed fore of the engine core and is rotatably connected to the engine core via a shaft. The engine pylon is disposed within a bifurcation and intersects a fan stream of the fan. The engine pylon includes a pylon space. At least one heat exchanger is disposed within the pylon space. The heat exchanger includes a first inlet connected to the at least one actively cooled engine system and a first outlet connected to the at least one actively cooled engine system.

Abstract: An auxiliary gearbox has a low speed input shaft driving a first plurality of accessories. A high speed input shaft drives a second plurality of accessories. The first plurality of accessories rotating about a first set of rotational axes, which are parallel to each other and perpendicular to a first plane. The second plurality of accessories rotating about a second set of rotational axes, which are parallel to each other and perpendicular to a second plane. The first and second planes extending in opposed directions away from a drive input axis of the high speed input shaft and the low speed input shaft. The low speed input shaft drives a variable speed transmission. A gas turbine engine is also disclosed.

Abstract: A gas turbine engine includes a low speed input shaft connected to a low speed tower shaft, in turn connected to a lower speed spool and a high speed input connected to a high speed tower shaft, in turn connected to a higher speed spool. The low speed input shaft is connected to drive a first plurality of accessories. The high speed input shaft is connected to drive a second plurality of accessories. The high speed tower shaft and the low speed tower shaft are coaxial and rotate about a common axis. An angle drive is provided into the low speed input shaft and the high speed input shaft, respectively.

Abstract: A gas turbine engine has a low speed input shaft drives a first plurality of accessories. A high speed input shaft drives a second plurality of accessories. The first plurality of accessories rotating about a first set of rotational axes perpendicular to a first plane. The second plurality of accessories rotating about a second set rotational axes perpendicular to a second plane. The first and second planes extending in opposed directions away from a drive input axis. Compressed air is tapped and passes through a heat exchanger, then to a boost compressor, and then to at least one rotatable components in a main compressor section and a main turbine section. The boost compressor driven on a boost axis, which is non-parallel to the first set of rotational axes and the second set of rotational axes.

Abstract: Aspects of the disclosure are directed to components of an engine and one or more methods for assembling the components. A first component is positioned adjacent to a second component such that a first surface of the first component abuts the second component. A cooling plate is coupled to the first component such that a first surface of the cooling plate abuts a second surface of the first component. A loading ram is coupled to the cooling plate such that a second surface of the cooling plate abuts the loading ram.

Abstract: A gearbox assembly for a gas turbofan engine includes a sun gear rotatable about an axis and a plurality of intermediate gears driven by the sun gear. A baffle disposed between at least two of the plurality of intermediate gears includes a first gap distance within a first gap portion and a second gap distance within a second gap portion. The first gap portion is disposed between the baffle and one of the intermediate gears away from the meshed interface with the sun gear and the second gap portion is disposed near the interface with the sun gear. The first gap distance within the first gap portion is different than the second gap distance within the second gap portion to define a desired lubricant flow path.

Abstract: A gas turbine engine includes an offset core and a propulsion assembly. The offset core is configured to rotate about a first axis. The propulsion assembly includes a fan section and a low-pressure turbine connected to the offset core. The fan section is in communication with the low-pressure turbine by a shaft configured to rotate about a second axis, different than the first axis. The shaft includes a nosecone inlet duct, an inner channel, and at least one shaft vent. The nosecone inlet duct is disposed within the fan section. The inner channel extends along a length of the shaft between the nosecone inlet duct and at least one air duct. The at least one shaft vent is disposed within the at least one air duct. The at least one air duct is configured to deliver air from the nosecone inlet duct to at least one heat exchanger.

Abstract: A power extraction system for a gas turbine engine may comprise a high spool transmission, a low spool transmission, and an accessory gearbox. The accessory gearbox may comprise a starter-generator, a low spool starter-generator gear, a high spool gear, and a clutch configured to selectively engage and disengage the low spool starter-generator gear and the high spool gear. The low spool starter-generator gear may be configured to transfer torque between the starter-generator and the low spool transmission for accessory power generation. The high spool gear may be configured to transfer torque to the high spool transmission for engine starting. The clutch may be controlled by a variable transmission and may allow accessories to be driven by the low spool after starting.

Abstract: A method of operating an aircraft according to an exemplary embodiment of this disclosure includes, among other possible things, communicating power from a storage device within an unmoved aerial vehicle (UAV) to an aircraft; controlling a propulsive device within the UAV with a control system of the aircraft to provide propulsive thrust to the aircraft; and detaching the UAV including the storage device and the propulsion device from the aircraft responsive to the energy within the storage device being below a predefined threshold.

Abstract: A gas turbine includes a shaft, a turbine coupled with the shaft for rotation with the shaft, and a bearing coupled with the shaft to facilitate rotation of the shaft. A bearing nut is adjacent the bearing on the shaft. The turbine has a first load path and the bearing has a second load path. The bearing nut exerts a force on the bearing such that the first load path is not aligned with the second load path relative to a central axis of the gas turbine engine. A method of assembling a gas turbine engine is also disclosed.

Abstract: Aspects of the disclosure are directed to a cover configured to substantially conform to a profile of a first assembly of an engine in terms of the dimensions of the first assembly and hermetically seal the first assembly such that a second assembly of the engine that is external to the cover is accessible, a container containing a desiccant, and a screen coupled to the container.

Abstract: A turbofan engine includes a fan rotatable about an axis, a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the combustor, a fan drive gear system including a carrier for supporting a plurality of gears, and a scupper capturing lubricant during gear operation and directing lubricant into the carrier. A fan drive gear system is also disclosed.

Abstract: A gearbox assembly for a gas turbofan engine includes a sun gear rotatable about an axis and a plurality of intermediate gears driven by the sun gear. A baffle disposed between at least two of the plurality of intermediate gears includes a first gap distance within a first gap portion and a second gap distance within a second gap portion. The first gap portion is disposed between the baffle and one of the intermediate gears away from the meshed interface with the sun gear and the second gap portion is disposed near the interface with the sun gear. The first gap distance within the first gap portion is different than the second gap distance within the second gap portion to define a desired lubricant flow path.

Abstract: A power extraction system for a gas turbine engine may comprise a high spool transmission, a low spool transmission, and an accessory gearbox. The accessory gearbox may comprise a starter-generator, a low spool starter-generator gear, a high spool gear, and a clutch configured to selectively engage and disengage the low spool starter-generator gear and the high spool gear. The low spool starter-generator gear may be configured to transfer torque between the starter-generator and the low spool transmission for accessory power generation. The high spool gear may be configured to transfer torque to the high spool transmission for engine starting. The clutch may be controlled by a variable transmission and may allow accessories to be driven by the low spool after starting.