Abstract: An apparatus is provided for an aircraft. This apparatus includes an electric machine and an air cooling circuit. The electric machine includes an electric machine rotor and an electric machine stator. The electric machine is configured to generate an electromagnetic field with the electric machine rotor and the electric machine stator. The electric machine rotor is configured to rotate about an axis. The air cooling circuit includes a cooling boot. The air cooling circuit is configured to direct air from an air source into the cooling boot. The cooling boot forms an air plenum with an exterior surface of the electric machine. The cooling boot includes a plurality of air outlets. The cooling boot is configured to direct the air through the air outlets and into the air plenum to air cool the electric machine.

Abstract: An assembly is provided for an aircraft. This assembly includes an engine core, an engine case, a nacelle wall and an air circuit. The engine core includes a compressor section, a combustor section and a turbine section. The engine case houses the engine core. The nacelle wall is radially outboard of and covers the engine case. A compartment is formed by and extends radially between the engine case and the nacelle wall. The air circuit includes a manifold disposed within the compartment. The air circuit is configured to direct air from an air source into the manifold. The manifold includes a plurality of outlets. The manifold is configured to direct the air into the compartment through the outlets.

Abstract: An apparatus is provided for an aircraft. This apparatus includes a turbine engine, a first electric machine, a first controller, a second electric machine, a second controller and a first fluid circuit. The first electric machine is operatively coupled to the turbine engine. The first controller is configured to control operation of the first electric machine. The second electric machine is operatively coupled to the turbine engine. The second controller is configured to control operation of the second electric machine. The first fluid circuit is configured to circulate a first liquid to cool and/or lubricate the first electric machine, the first controller, the second electric machine and the second controller.

Abstract: An aircraft apparatus includes a turbine engine, a first electric machine, a first controller, a first fluid circuit, a second electric machine, a second controller and a second fluid circuit. The turbine engine includes a first rotating structure and a second rotating structure. The first electric machine is operatively coupled to the first rotating structure. The first controller is configured to control operation of the first electric machine. The first fluid circuit is configured to circulate a first liquid and service the first electric machine and the first controller. The second electric machine is operatively coupled to the second rotating structure. The second controller is configured to control operation of the second electric machine. The second fluid circuit is configured to circulate a second liquid and service the second electric machine and the second controller. The second fluid circuit is fluidly discrete from the first fluid circuit.

Abstract: A system includes a turbine engine, a low spool gearbox, and a high spool gearbox. The system also includes a first lubrication system configured to serve the low spool gearbox, and a second lubrication system, independent from the first lubrication system, configured to serve the high spool gearbox. The turbine engine includes a low-pressure spool and a high-pressure spool. The low spool gearbox is disposed within a core compartment of the turbine engine. The low spool gearbox is configured to transfer mechanical power between the low-pressure spool and a first accessory. The high spool gearbox is disposed within the core compartment of the turbine engine. The high spool gearbox is configured to transfer mechanical power between the high-pressure spool and a second accessory.

Abstract: An aircraft assembly includes a turbine engine, a first electric machine, a first controller, an electric machine fluid circuit and a controller fluid circuit. The turbine engine includes a compressor section, a combustor section, a turbine section, a flowpath and a first rotating structure. The first rotating structure includes a first bladed rotor disposed in one of the compressor section or the turbine section. The first electric machine includes a first electric machine rotor. The first electric machine rotor is operatively coupled to the first rotating structure. The first controller is configured to electrically couple the first electric machine to an electrical system. The electric machine fluid circuit is configured to circulate a first liquid and service the first electric machine. The controller fluid circuit is configured to circulate a second liquid and service the first controller. The controller fluid circuit is fluidly discrete from the electric machine fluid circuit.

Abstract: An apparatus is provided for an aircraft that includes an open rotor propulsion system. The open rotor propulsion system includes a turbine engine, a first electric machine, a second electric machine, a first controller, a second controller and a first fluid circuit. The first controller is configured to control operation of the first electric machine. The second controller is configured to control operation of the second electric machine. The first fluid circuit is configured to circulate a first liquid to cool and/or lubricate the first electric machine, the first controller, the second electric machine and the second controller.

Abstract: An aircraft assembly includes a propulsor rotor, a turbine engine core, an inner case, an outer case, a first gearbox, a second gearbox, a first electric machine and a second electric machine. The turbine engine core is configured to drive rotation of the propulsor rotor about an axis. The turbine engine core includes a first rotating structure and a second rotating structure. The first rotating structure includes a first bladed rotor. The second rotating structure includes a second bladed rotor. The inner case houses the turbine engine core. The outer case houses the propulsor rotor. The first gearbox is mounted with the outer case. The second gearbox is mounted with the outer case. The first electric machine is operatively coupled to the first rotating structure through the first gearbox. The second electric machine is operatively coupled to the second rotating structure through the second gearbox.

Abstract: An aircraft assembly is provided that includes a propulsor rotor, a turbine engine core, an inner case, a first gearbox, a second gearbox, a first electric machine and a second electric machine. The turbine engine core includes a first rotating structure and a second rotating structure. The first gearbox is mounted with the inner case. The second gearbox is located remote from the inner case. The first electric machine is operatively coupled to the first rotating structure through the first gearbox. The second electric machine is operatively coupled to the second rotating structure through the second gearbox. The first electric machine may be configurable as a first electric motor and/or a first electric generator. In addition or alternatively, the second electric machine may be configurable as a second electric motor and/or a second electric generator.

Abstract: An aircraft powerplant system includes a turbine engine and an accessory system. The turbine engine includes a core flowpath, a first rotating structure, a compressor section, a combustor section and a turbine section. The first rotating structure includes a first bladed rotor arranged along the core flowpath in the compressor section or the turbine section. The accessory system includes a first electromechanical apparatus, an air circuit and an air device. The first electromechanical apparatus includes a first electric machine and a first boost compressor. The first electric machine includes a first electric machine rotor that is operatively coupled to the first rotating structure. The first boost compressor includes a first boost compressor rotor that is operatively coupled to the first electric machine rotor and the first rotating structure. The air circuit is configured to direct air received from an air source, through the first boost compressor, to the air device.

Abstract: A vane structure includes a structure passage that extends internally from a passage inlet to a passage outlet. The passage inlet fluidly couples the structure passage to an external environment outside of the vane structure. The first heat exchanger is disposed within the vane structure along the structure passage between the passage inlet and the passage outlet. The second heat exchanger is disposed within the vane structure along the structure passage between the passage inlet and the passage outlet. The electric machine system includes a plurality of electric components including a first electric machine and a first electric machine controller for the first electric machine. The first electric machine is configurable as an electric motor and/or an electric generator. The first fluid circuit is configured to cool and/or lubricate a first of the electric components. The first fluid circuit includes the first heat exchanger and/or the second heat exchanger.

Abstract: An aircraft assembly includes an engine core, a first electrical power system and a second electrical power system. The first electrical power system includes a first electric machine and a first electric machine controller. The first electric machine is operatively coupled to the engine core. The first electric machine controller is electrically coupled to the first electric machine. The first electric machine controller is configured to control operation of the first electric machine. The second electrical power system is electrically discrete from the first electrical power system. The second electrical power system includes a second electric machine and a second electric machine controller. The second electric machine is operatively coupled to the engine core. The second electric machine controller is electrically coupled to the second electric machine. The second electric machine controller is configured to control operation of the second electric machine.

Abstract: An assembly is provided for an aircraft powerplant. This assembly includes a vane structure, a first electric device and a cooling system. The first electric device is disposed within the vane structure. The first electric device includes a first device housing and first electrical circuitry. The first electrical circuitry is housed within an interior of the first device housing. The cooling system is configured to cool the first electrical circuitry. The cooling system includes a first heat exchanger and an air circuit. The first heat exchanger is disposed within the vane structure and thermally coupled to the first electric device. The air circuit extends within the vane structure from an airflow inlet into the air circuit, through the first heat exchanger, to an airflow outlet from the air circuit. The airflow inlet fluidly couples the air circuit to a volume external to the vane structure.

Abstract: A hybrid-electric aircraft propulsion system includes an engine, a first electric machine assembly, and a second electric machine assembly. The engine includes a first rotational assembly and a second rotational assembly. The first electric machine assembly includes a first electric machine, a first control unit, first electrical cables, and a first cable conduit. The first electric machine is coupled with the first rotational assembly. The first electrical cables extend between and electrically connect the first electric machine and the first control unit through the first cable conduit. The second electric machine assembly includes a second electric machine, a second control unit, second electrical cables, and a second cable conduit. The second electric machine is coupled with the second rotational assembly. The second electrical cables extend between and electrically connect the second electric machine and the second control unit through the second cable conduit.

Abstract: A gas turbine engine is provided that includes compressor and turbine sections, and a turbine cooling air (TCA) system. The turbine section has upstream and downstream rotor stages, and turbine sub-sections. The TCA system includes a flow mixing device and a compressor bleed air flow valve, and is configured to receive first and second compressor bleed air flows. The compressor bleed air flow valve may be in an open or a closed configuration. The TCA system operates in a first or a second mode. In the first mode, the compressor bleed air flow valve is closed and a conditioned air flow is from the first compressor bleed air flow. In the second mode, the compressor bleed air flow valve is open and the conditioned air flow is a mixture of the first and second compressor bleed air flows. The conditioned air flow is directed to the downstream turbine sub-section.

Abstract: A gas turbine engine is provided that includes fan, compressor, combustion, and turbine sections, a fan bypass air path, and a turbine active clearance control system. The turbine section has a rotor stage and a turbine case clearance control segment. The turbine active clearance control system includes a bleed air mixing system, a fan bypass air inlet device configured to receive a fan bypass air flow, and a compressor air bleed structure configured to receive a compressor bleed air flow. The turbine active clearance control system is configurable in a turbine case heating mode in which the bleed air mixing system mixes the fan bypass air flow and the compressor bleed air flow to produce a conditioned air flow that is operable to heat the turbine case clearance control segment. The turbine active clearance control system directs the conditioned air flow to the turbine case clearance control segment.

Abstract: A gas turbine engine disposed within a nacelle is provided that includes an open rotor propulsion system, compressor, combustion, and turbine sections, and a turbine active clearance control system. The turbine section has a turbine case clearance control segment disposed radially outside of a rotor stage. The turbine active clearance control system includes a bleed air mixing system, a nacelle air inlet device, and a compressor air bleed structure. The turbine active clearance control system is configurable in a turbine case heating mode in which the bleed air mixing system is used to mix an exterior air flow and a compressor bleed air flow to produce a conditioned air flow that is operable to heat the turbine case clearance control segment, and the turbine active clearance control system is configured to direct the conditioned air flow to the turbine case clearance control segment.

Abstract: A gas turbine engine is provided that includes a fan, compressor, combustion, and turbine sections, a fan bypass air path, a lubrication system, and a turbine active clearance control (ACC) system. The turbine section has a rotor stage and a turbine case clearance control segment. The turbine ACC system includes first and second valves and a heat exchanger. The heat exchanger may receive a first fan bypass air flow and a lubricant flow and permits heat transfer therebetween to produce a flow of conditioned air. The first valve receives conditioned air from the heat exchanger. The second valve may receive conditioned air and a second fan bypass air flow. The turbine ACC system may operate in a heating mode in which conditioned air flow, or a combination of conditioned air flow and the second fan bypass air flow is passed to the turbine case clearance control segment.

Abstract: A propulsion system for an aircraft includes a gas turbine engine, an electrical assembly, a powertrain, and a controller. The gas turbine engine includes a rotational structure and a second rotational structure each including a turbine rotor. The electrical assembly includes an electric machine and a control unit. The control unit is electrically connected to the electric machine. The powertrain includes a differential geartrain configured to couple the rotational structure and the second rotational structure together to the electric machine. The controller is connected in communication with the control unit. The controller is configured to maintain a predetermined power transfer ratio between a spool mechanical power transfer of the second rotational structure and an electric machine mechanical power transfer of the electric machine along a rotation speed range of the second rotational structure by controlling an electrical loading of the electric machine with the control unit.

Abstract: An aircraft powerplant assembly includes a gearbox, a first electric machine, a first electric cable, a second electric machine and a second electric cable. The first electric machine is mounted to the gearbox at a first side of the gearbox. A first machine terminal is disposed at a first side of the first electric machine. The first electric cable is electrically coupled to the first machine stator through the first machine terminal. The second electric machine is mounted to the gearbox at the first side of the gearbox. A second machine terminal is disposed at a second side of the second electric machine that faces the first side of the first electric machine. The second electric cable is electrically coupled to the second machine stator through the second machine terminal.