Abstract: A gas turbine engine is provided having an axial centerline, a compressor section, a turbine section, and a combustor section. The turbine section has a turbine first vane assembly that includes an annular first vane inner radial support. The combustor section has an outer casing, an annular combustor, and a unitary inner diffuser structure. The annular combustor has an inner radial flange. The unitary inner diffuser structure includes a compressor discharge, an inner diffuser case, and a tangential onboard injector (TOBI) inseparably attached to one another. The unitary inner diffuser structure further includes an outer radial flange and a TOBI connection flange. The annular FV inner radial support, the combustor inner radial flange, and the TOBI connection flange are secured to one another.

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, a heat exchange passage and a plurality of cooling elements. The heat exchange passage extends longitudinally along a centerline of the heat exchange passage from the inlet manifold to the outlet manifold. The cooling elements are distributed longitudinally and laterally along the heat exchange passage in a cooling element array. The electric machine controller includes a controller housing and controller circuitry. The controller housing is removably attached to the cooling plate and overlaps the cooling element array. 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: An assembly is provided for an aircraft powerplant. This aircraft powerplant assembly includes a compressor section, a combustor section, a turbine section, a flowpath, a first rotating structure, a second rotating structure, a differential geartrain and an electric machine. The flowpath extends through the compressor section, the combustor section and the turbine section. The first rotating structure includes a first turbine rotor arranged along the flowpath in the turbine section. The second rotating structure includes a second turbine rotor arranged along the flowpath in the turbine section. The differential geartrain is operatively coupled to the first rotating structure and the second rotating structure. The electric machine includes an electric machine rotor. The electric machine rotor is integrated with the differential geartrain.

Abstract: An aircraft propulsion system includes a gas turbine engine, a propulsor rotor, and an electrical assembly. The gas turbine engine forms a core flowpath along an axis. The gas turbine engine further includes a first rotating structure and a third rotating structure. The first rotating structure includes a bladed first compressor rotor and a bladed first turbine rotor. The third rotating structure includes a bladed third turbine rotor downstream of the bladed first turbine rotor. The third rotating structure is axially separate from the first rotating structure. The propulsor rotor is mechanically independent of the gas turbine engine. The electrical assembly includes a first electric machine and a third electric machine. The first electric machine is operably coupled with the propulsor rotor. The third electric machine is operably coupled with the third rotating structure. The first electric machine is electrically connected with the third electric machine.

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 powerplant includes a turbine engine, a first fluid system, an electric machine system, a second fluid system, a heat exchanger and a control system. The first fluid system directs a first fluid through the first fluid circuit using a first fluid pump to service engine components during a warmup mode. The electric machine system includes an electric machine configured to drive operation of the first fluid pump during the warmup mode. The second fluid system directs a second fluid through a second fluid circuit such that electronics heat energy generated by power electronics is transferred into the second fluid and cools the power electronics during the warmup mode. The heat exchanger is configured to transfer the electronics heat energy from the second fluid in the second fluid circuit into the first fluid in the first fluid circuit to heat the first fluid during the warmup mode.

Abstract: A system is provided for an aircraft. This system includes a turbine engine and a cooling system. The turbine engine extends axially along an axis. The turbine engine includes a core flowpath, a compressor section, a combustor section and a turbine section. The core flowpath extends through the compressor section, the combustor section and the turbine section from an airflow inlet into the core flowpath to a combustion products exhaust from the core flowpath. The cooling system is configured to air cool the turbine engine following shutdown of the turbine engine. The cooling system includes a plurality of electric air movers. The electric air movers are arranged axially along the turbine engine.

Abstract: An assembly is provided for an aircraft powerplant. This assembly includes a compressor section, a combustor section, a turbine section, a flowpath, a first rotating structure, a second rotating structure, a first electric machine and a differential. The flowpath extends through the compressor section, the combustor section and the turbine section. The first rotating structure includes a first turbine rotor arranged along the flowpath in the turbine section. The second rotating structure includes a second turbine rotor arranged along the flowpath in the turbine section. The first electric machine includes a first electric machine rotor coaxial with the first rotating structure and the second rotating structure. The differential geartrain operatively couples the first electric machine rotor to the first rotating structure and the second rotating structure.

Abstract: An aircraft powerplant assembly includes a first engine rotating structure, a second engine rotating structure, a gearbox, a first lubrication system and a second lubrication system. The gearbox includes a gearbox housing, a first gear system and a second gear system. The gearbox housing includes a first compartment and a second compartment fluidly decoupled from the first compartment. The first gear system is in the first compartment and is coupled to the first engine rotating structure. The second gear system is in the second compartment and is coupled to the second engine rotating structure. The first lubrication system is configured to lubricate the first gear system and is fluidly coupled to the first compartment. The second lubrication system is configured to lubricate the second gear system and is fluidly coupled to the second compartment. The second lubrication system is fluidly decoupled from the first lubrication system.

Abstract: A gas turbine engine is provided that includes first and second spools, an accessory gearbox, first and second electric motors, and a motor controller system. The accessory gearbox is in drive communication with the first and second spools. The first and second electric motors are mounted on the accessory gearbox. The motor controller system includes a first MCU, a second MCU, and a lubrication system. The first MCU includes a first motor drive and a first pump motor drive. The second MCU includes a second motor drive and a second pump motor drive. The lubrication system includes a pump with an electric pump motor. The lubrication system is configured to operate in a first mode wherein the pump is controlled by the first MCU and in a second mode wherein the pump is controlled by the second MCU.

Abstract: An assembly is provided for an aircraft powerplant. This assembly includes an engine case, a combustor and a thermoelectric generator. The engine case extends axially along and circumferentially around an axis. The engine case forms an outer peripheral boundary of a diffuser plenum. The combustor is disposed in the diffuser plenum. The combustor includes a combustor wall and a combustion chamber within the combustor. The combustor wall borders the diffuser plenum and forms an outer peripheral boundary of the combustion chamber. The thermoelectric generator is arranged in the diffuser plenum. The thermoelectric generator is located radially between and is spaced radially from the combustor wall and the engine case. The thermoelectric generator is configured to convert heat energy radiated out from the combustor into electricity.

Abstract: An aircraft powerplant system includes a heat exchanger, a fluid circuit and an air system. The fluid circuit extends through the heat exchanger. The air system includes a first circuit leg, a second circuit leg, a third circuit leg and a flow regulator. The second circuit leg is arranged with the heat exchanger. The flow regulator is fluidly coupled between the first circuit leg, the second circuit leg and the third circuit leg. The air system is configured to receive air from an air source and direct the air sequentially through the first circuit leg, the flow regulator and the second circuit leg during a first mode of operation. The air system is configured to receive the air from the air source and direct the air sequentially through the second circuit leg, the flow regulator and the third circuit leg during a second mode of operation.

Abstract: A method is provided for operating an aircraft system. During this method, a first temperature of a lubricant is determined. The aircraft system is operated in a first warmup mode when the first temperature of the lubricant is below a first threshold. The operating of the aircraft system in the first warmup mode includes driving rotation of a rotating structure about an axis and heating the first quantity of the lubricant contained in the first reservoir using a first electric heater. A startup of the turbine engine is initiated following the operating of the aircraft system in the first warmup mode.

Abstract: An aircraft powerplant assembly includes a rotor, a shroud, a casing, a structure and an air system. The structure circumscribes the casing with a plurality of air plenums formed by and disposed radially between the structure and the casing. The air plenums are arranged circumferentially around the axis in an array. The air plenums include a first plenum and a second plenum. The air system is configured to control a clearance between the shroud and an array of rotor blades using air. The air system includes a first air circuit and a second air circuit. The first air circuit is configured to direct a first flow of the air into the first plenum to cool a first section of the casing. The second air circuit is configured to direct a second flow of the air into the second plenum to cool a second section of the casing.

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 method is provided for operating a turbine engine. During this method, a bladed turbine rotor is rotated about an axis. A turbine shroud is next to and circumscribes the bladed turbine rotor. A clearance is controlled between the bladed turbine rotor and the turbine shroud using a clearance control system. Operation of the clearance control system is tuned during turbine engine operation based on a change in an engine operating parameter over a period of time.

Abstract: An aircraft powerplant assembly includes a first electric device and a cooling system. The first electric device includes a first device heat exchanger, a first device housing and first electrical circuitry. The cooling system includes a liquid circuit, an air circuit and a system heat exchanger. The cooling system is configured to cool the first electrical circuitry using a liquid flowing in the liquid circuit and air flowing in the air circuit. The liquid circuit extends through the system heat exchanger and the first electric device. The first device heat exchanger is configured to transfer heat energy from the first electrical circuitry into the liquid in the liquid circuit. The air circuit extends through the system heat exchanger. The system heat exchanger is configured to transfer at least some of the heat energy from the liquid in the liquid circuit into the air in the air circuit.

Abstract: A propulsion system includes a gas turbine engine, a nacelle, a bifurcation, an electrical assembly, and a thermal management assembly. The gas turbine engine includes a rotational assembly and an engine static structure. The engine static structure houses the rotational assembly. The nacelle forms an annular bypass duct radially between the engine static structure and the nacelle. The bifurcation extends between the engine static structure and the nacelle. The electrical assembly includes an electric machine and a control unit. The electric machine is coupled with the rotational assembly. The control unit is electrically connected to the electric machine. The control unit is disposed within the bifurcation. The thermal management assembly includes a control unit cooling circuit. The control unit cooling circuit is connected in fluid communication with and formed by the control unit. The control unit cooling circuit is disposed within the bifurcation.

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.