Abstract: An aircraft powerplant assembly includes a gearbox and a power coupler. The gearbox includes a first power transfer apparatus and a second power transfer apparatus. The first power transfer apparatus is configured to couple and transfer first mechanical power through the gearbox between a first engine apparatus and a first engine accessory. The second power transfer apparatus is configured to couple and transfer second mechanical power through the gearbox between a second engine apparatus and a second engine accessory during a first mode. The power coupler includes a variable speed transmission and a clutch. The variable speed transmission is coupled between the clutch and the second power transfer apparatus. The clutch is configured to couple the variable speed transmission to the second engine apparatus during the first mode. The clutch is configured to decouple the variable speed transmission from the second engine apparatus during a second mode.

Abstract: A propulsion system for an aircraft includes a propulsor rotor, a powerplant, a nacelle and a lockout system. The powerplant is coupled to and configured to drive rotation of the propulsor rotor. An electrical system for the powerplant is configured to receive electrical power from an electrical power source. The nacelle includes an access structure configured to move between a first position and a second position. The access structure at least partially covers the electrical system when in the first position. The access structure is arranged in the first position for propulsion system operation. The access structure is operable to be arranged in the second position for propulsion system maintenance and/or propulsion system inspection. The lockout system is configured to automatically trigger an operation to cut off the electrical power to the electrical system from the electrical power source when the access structure moves away from the first position.

Abstract: A system for and method of operating a propulsion system for an aircraft is provided. The propulsion system includes a gas turbine engine, an accessory gearbox, and an electric motor. The gas turbine engine includes a spool having a fan rotor with a plurality of fan blades, and a pitch control mechanism engaged with the fan blades. The method includes: providing rotational drive from the spool to the accessory gearbox; using the accessory gearbox to drive an electric motor to produce electrical energy, wherein the electric motor has a predetermined maximum rotational speed limit; and controlling the propulsion system to follow a predetermined descent portion of a flight profile for the aircraft, wherein controlling the propulsion system includes controlling the pitch control mechanism to alter an amount of thrust produced by the fan blades by altering a pitch of the fan blades.

Abstract: An assembly is provided for an aircraft powerplant. This assembly includes an aircraft engine, a control system and a conduit. The control system includes an electronic engine controller, a first electric device and a first electric cable electrically coupling the first electric device to the electronic engine controller. The electronic engine controller is configured to control operation of the aircraft engine using the first electric device. The conduit extends longitudinally from a first end of the conduit to a second end of the conduit. The first electric cable extends longitudinally in a bore of the conduit between the electronic engine controller and the first electric device. The conduit is configured to shield the first electric cable from electromagnetic interference generated outside of the conduit.

Abstract: A gas turbine engine is provided that includes first and second spools, an accessory gearbox, and a spool coupling device. The first spool includes a first compressor section and a first turbine section. The second spool includes a second compressor section and a second turbine section. The accessory gearbox (AG) is in drive communication with the second spool. The accessory gearbox includes an AG output shaft. The spool coupling device (SCD) is in drive communication with the first spool and the AG output shaft. The spool coupling device includes an SCD accessory dock and a transmission that is disposable in first or second spool engaged configurations. In the first spool engaged configuration, rotational drive from the first spool is provided to the SCD accessory dock, and in the second spool engaged configuration, rotational drive from the second spool is provided to the SCD accessory dock.

Abstract: A gas turbine engine includes an engine core with a compressor section, a combustion section downstream of the compressor section relative to a core flow path, and a turbine section downstream of the combustion section relative to the core flow path. A core casing extends around the compressor section, the combustion section, and the turbine section. A second casing extends around the core casing and a core compartment is between the core casing and the second casing. An electric compressor is in the core compartment. A first port is formed in the second casing and fluidically is connected to the electric compressor. A second port is formed in the core casing in the combustion section and is fluidically connected to the electric compressor.

Abstract: A hybrid-electric aircraft propulsion system includes a gas turbine engine, an electrical assembly, and a gear train. The gas turbine engine includes a first rotational assembly rotatable about a rotational axis of the gas turbine engine. The electrical assembly includes a plurality of electric machines. The plurality of electric machines includes a first electric machine and a second electric machine. The gear train includes a first shaft, a second shaft, a third shaft, a first gear, a second gear, and a transmission assembly. The first shaft couples the first electric machine with the first rotational assembly. The second shaft is coupled with the second electric machine. The second shaft is selectively coupled with the third shaft by the transmission assembly. The first gear is mounted on the first shaft. The second gear is mounted on the third shaft and engaged with the first gear.

Abstract: A propulsion system includes an electrical assembly. The electrical assembly includes an electric machine, a control unit, and a thermal management assembly. The control unit is electrically connected to the electric machine. The thermal management assembly includes an electric machine cooling circuit, a control unit (CU) cooling circuit, and a pump assembly. The electric machine cooling circuit is connected in fluid communication with the electric machine. The CU cooling circuit is connected in fluid communication with the control unit. The pump assembly includes a pump shaft, a first pump rotor, and a second pump rotor. The first pump rotor and the second pump rotor are mounted on the pump shaft. The first pump rotor forms a coolant pump of the electric machine cooling circuit. The second pump rotor forms a coolant pump of the CU cooling circuit.

Abstract: An aircraft propulsion system includes a gas turbine engine, an electric machine, and a drive train. The gas turbine engine includes a first spool and a second spool. The electric machine includes a first rotor and a second rotor. The first rotor and the second rotor are concentric about a first axis. The drive train couples the first spool with the first rotor. The drive train is configured to couple the second spool with the second rotor. The drive train includes a tower shaft, a drive shaft, and an angled gear box. The tower shaft is coupled with the first spool. The tower shaft rotatable about a second axis. The drive shaft is operably coupled with the first rotor. The drive shaft is rotatable about a third axis transverse to the second axis. The angled gear box couples the tower shaft with the drive shaft.

Abstract: An aircraft propulsion system includes a gas turbine engine, a power transfer assembly, and a controller. The gas turbine engine includes a first spool and a second spool. The power transfer assembly includes a first motor-generator, a second motor-generator, and a motor control assembly. The first motor-generator is operably coupled with the first spool. The second motor-generator is operably coupled with the second spool. The motor control assembly is electrically connected to the first motor-generator and the second motor-generator. The motor control assembly is configured to control an operating voltage of the power transfer assembly. The controller is connected in signal communication with the motor control assembly. The is controller is configured to identify a target operating voltage of the power transfer assembly selected in response to an aircraft altitude input to the controller and control the motor control assembly to control the operating voltage at the target operating voltage.

Abstract: An aircraft propulsion system includes a gas turbine engine and a power transfer assembly. The gas turbine engine includes a high-pressure (HP) spool and a low-pressure (LP) spool. The power transfer assembly includes a first motor-generator, a second motor-generator, a motor control assembly, and a common assembly housing. The first motor-generator is operably coupled with the HP spool. The second motor-generator is operably coupled with the LP spool. The first motor-generator is electrically connected to the second motor-generator. The motor control assembly is electrically connected to the first motor-generator and the second motor-generator. The motor control assembly is configured to operate the first motor-generator to apply a first rotational force to the HP spool or to operate the second motor-generator to apply a second rotational force to the LP spool. The common assembly housing houses the first motor-generator and the second motor-generator.

Abstract: A gas turbine engine includes an engine core with a compressor section, a combustion section downstream of the compressor section relative to a core flow path, and a turbine section downstream of the combustion section relative to the core flow path. A core casing extends around the compressor section, the combustion section, and the turbine section. A second casing extends around the core casing and a core compartment is between the core casing and the second casing. An electric compressor is in the core compartment. A first port is formed in the second casing and fluidically is connected to the electric compressor. A second port is formed in the core casing in the combustion section and is fluidically connected to the electric compressor.

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: An assembly is provided for an aircraft powerplant. This assembly includes a gearbox, an engine accessory, an engine core, a motor accessory and an electric motor. The gearbox includes an engine power transfer system and a motor power transfer system independent of the engine power transfer system. The engine accessory includes an engine accessory rotor. The engine core includes a flowpath, a compressor section, a combustor section, a turbine section and an engine rotating assembly. The flowpath extends through the compressor section, the combustor section and the turbine section. The engine rotating assembly includes a turbine rotor in the turbine section. The engine rotating assembly is operatively coupled to the engine accessory rotor through the engine power transfer system. The motor accessory includes a motor accessory rotor. The electric motor includes an electric motor rotor operatively coupled to the motor accessory rotor through the motor power transfer system.

Abstract: An aircraft powerplant assembly includes a cooling plate, a first control valve and a first electric machine. The cooling plate includes a fluid cooling circuit, a cooling circuit inlet and a cooling circuit outlet. The fluid cooling circuit is disposed in the cooling plate and extends from the cooling circuit inlet to the cooling circuit outlet. The fluid cooling circuit includes a first circuit passage fluidly coupled between the cooling circuit inlet and the cooling circuit outlet. The first control valve is fluidly coupled between the cooling circuit inlet and the first circuit passage. A first controller housing is removably attached to the cooling plate and overlaps the first circuit passage. First controller circuitry is disposed within an interior of the first controller housing. The first controller circuitry is in thermal communication with the cooling plate through a wall of the first controller housing.

Abstract: An aircraft powerplant assembly includes a cooling plate, a first electric machine controller and a second electric machine controller. The cooling plate includes a fluid cooling circuit, a cooling circuit inlet and a cooling circuit outlet. The fluid cooling circuit extends within the cooling plate from the cooling circuit inlet to the cooling circuit outlet. A first controller housing is removably attached to the cooling plate and overlaps the fluid cooling circuit. First controller circuitry is in thermal communication with the cooling plate through a wall of the first controller housing. A second controller housing is removably attached to the cooling plate and overlaps the fluid cooling circuit. Second controller circuitry is in thermal communication with the cooling plate through a wall of the second controller housing.

Abstract: An aircraft powerplant assembly includes a cooling plate and an electric machine controller. The cooling plate includes a fluid cooling circuit internal to a body of the cooling plate. The fluid cooling circuit includes an inlet manifold, an outlet manifold and a plurality of heat exchange passages. Each of the heat exchange passages extends longitudinally along a longitudinal centerline from the inlet manifold to the outlet manifold. A first heat exchange passage is configured with a plurality of first cooling elements arranged longitudinally along its longitudinal centerline. The electric machine controller includes a controller housing and controller circuitry. The controller housing is removably attached to the cooling plate and overlaps the heat exchange passages. The controller circuitry is disposed within an interior of the controller housing. The controller circuitry is in thermal communication with the cooling plate through a wall of the controller housing.

Abstract: A propulsion system for an aircraft includes a propulsor rotor, a powerplant, a nacelle and a lockout system. The powerplant is coupled to and configured to drive rotation of the propulsor rotor. An electrical system for the powerplant is configured to receive electrical power from an electrical power source. The nacelle includes an access structure configured to move between a first position and a second position. The access structure at least partially covers the electrical system when in the first position. The access structure is arranged in the first position for propulsion system operation. The access structure is operable to be arranged in the second position for propulsion system maintenance and/or propulsion system inspection. The lockout system is configured to automatically trigger an operation to cut off the electrical power to the electrical system from the electrical power source when the access structure moves away from the first position.

Abstract: A modulated air flow heat exchanger system in a bifurcation duct including an air oil cooler located proximate the bifurcation duct; at least one door positioned upstream of the air oil cooler proximate the bifurcation duct, wherein the at least one door controls a flow of a fan discharge airflow through the air oil cooler; and an actuator in operative communication with the at least one door.

Abstract: A system for providing cooling air within a hybrid electric gas turbine engine includes at least one cooling air tube configured to provide high pressure turbine cooling air from a first location to a second location within the hybrid electric gas turbine engine. At least one throttling valve each located on the at least one cooling air tube configured to limit a flow of the high pressure turbine cooling air from the first location to the second location. At least one electromechanical actuator each associated with the at least one throttling valve configured to actuate the throttling valve to a first flow level when the hybrid electric gas turbine engine is in a first condition and to a second flow level when the hybrid electric gas turbine engine is in a second condition responsive to control signals from an external source.