Abstract: A hybrid-electric propulsion system for an aircraft is provided that includes a propulsion unit, a propulsion unit gear box, a gas turbine engine, and an electric motor drive system. The gas turbine engine has compressor, combustion, and turbine sections, and is configured to provide motive force to the propulsion unit gear box. The electric motor drive system is disposed to provide motive force to the propulsion gear box or to the gas turbine engine. The electric motor drive system (EMDS) is adapted to interchangeably use a plurality of EMDS packages, each EMDS package including an electric motor and a battery. The electric motor drive system has a set of performance parameters that vary depending upon the particular EMDS package that is used with the electric motor drive system. The electric motor drive system includes interfaces that allow each EMDS package to be interchangeably used.

Abstract: An aircraft system is provided that includes a compressor section, a combustor section, a turbine section, an exhaust duct and a flowpath. The exhaust duct includes an upstream duct section, a plurality of intermediate duct sections and a downstream duct section. A first of the intermediate duct sections is fluidly discrete from a second of the intermediate duct sections. The intermediate duct sections are fluidly coupled in parallel between the upstream duct section and the downstream duct section. The flowpath extends sequentially longitudinally through the compressor section, the combustor section, the turbine section, the upstream duct section, the intermediate duct sections and the downstream duct section from an inlet into the flowpath to an outlet from the flowpath.

Abstract: An aircraft system is provided that includes a compressor section, a combustor section, a turbine section, an exhaust duct and a flowpath. The exhaust duct includes an upstream duct section, a plurality of intermediate duct sections and a downstream duct section. A first of the intermediate duct sections is fluidly discrete from a second of the intermediate duct sections. The intermediate duct sections are fluidly coupled in parallel between the upstream duct section and the downstream duct section. The flowpath extends sequentially longitudinally through the compressor section, the combustor section, the turbine section, the upstream duct section, the intermediate duct sections and the downstream duct section from an inlet into the flowpath to an outlet from the flowpath.

Abstract: The aircraft can have a cabin adapted to receive one or more persons; a rotary airfoil device; an electric engine drivingly coupled to the rotary airfoil device; a battery powering the electric engine; a coolant subsystem having a coolant circuit and a coolant pump operable to circulate a coolant in the coolant circuit, the coolant circuit connected in heat exchange relationship with at least one of the electric engine and the battery; a heat pump having a refrigerant circuit fluidly connecting, in sequence, a compressor, a condenser, an expansion valve, a first evaporator, and an environmental control line branching off from the refrigerant circuit between the condenser and the first evaporator, the environmental control line having a second evaporator and reconnected to the refrigerant circuit between the first evaporator and the compressor, the first evaporator connected in heat exchange relationship with the coolant circuit; and a pressurized air subsystem having a pressurized air line operable to deliver

Abstract: A hybrid aircraft power plant includes an air mover for propelling an aircraft, a gas turbine engine operable to drive the air mover, and an electric machine operable as a motor to drive the air mover. The gas turbine engine includes a turbine disk for extracting energy from a stream of combustion gas and an exhaust duct defining: an exhaust passage for conveying the stream of combustion gas from the turbine disk; and a cavity disposed radially inward of the exhaust passage. A shaft drivingly connects the turbine disk with the electric machine and extends inside the cavity defined by the exhaust duct. A fan is drivingly connected to the shaft and operable to circulate cooling air inside the cavity of the exhaust duct.

Abstract: An assembly for a propulsion system of an aircraft includes an electric motor, a first gearbox module, a second gearbox module, and a propeller. The electric motor includes a rotor. The rotor includes a first axial end and a second axial end. The first gearbox module includes a first gear assembly. The first gear assembly is coupled to the first axial end. The second gearbox module includes a second gear assembly. The second gear assembly is coupled to the second axial end. The propeller is coupled to the first gear assembly. The first gear assembly is configured to drive rotation of the propeller in response to rotation of the rotor.

Abstract: An assembly for an aircraft powerplant includes a compressor rotor and an air system. The compressor rotor includes a plurality of compressor blades. The compressor blades are arranged circumferentially around the axis in a compressor blade array and are disposed in a flowpath. The air system includes an air source, an air injector and an air circuit fluidly coupling the air source to the air injector. The air system is configured to direct compressed air from the air source to the air injector through the air circuit. The air injector is configured to direct a stream of the compressed air into the flowpath and against one or more of the compressor blades to apply a rotational driving force onto the compressor rotor about an axis. The flowpath has a radial height at an injector location. The air injector projects a radial distance into the flowpath at the injector location.

Abstract: A propulsion system for an aircraft is provided. The propulsion system includes a propulsion rotor, and at least one engine mechanically coupled to the propulsion rotor via a geartrain. The propulsion system also includes a first propulsor module having a first housing, a first electric motor, and a first bladed propulsor. The first bladed propulsor is coupled with the first electric motor within the first housing. The propulsion system further includes a second propulsor module having a second housing, a second electric motor, and a second bladed propulsor. The second bladed propulsor is coupled with the second electric motor within the second housing. The propulsion system also includes a first generator driven by the at least one engine and electrically connected with the first electric motor. Additionally, the propulsion system includes a second generator driven by the at least one engine and electrically connected with the second electric motor.

Abstract: A propulsion system for an aircraft includes a propulsion rotor, an engine, a propulsor module, and a blended exhaust system. The engine has an axis, is mechanically coupled to the propulsion rotor, and includes an exhaust section. The propulsor module includes a housing forming a propulsor duct with a duct inlet and duct outlet, and a propulsor assembly with an electric motor coupled to a bladed propulsor disposed within the propulsor duct. The blended exhaust system includes an exhaust duct assembly having an engine exhaust inlet at the exhaust section, a propulsor exhaust inlet at the duct outlet, and a blended exhaust outlet. The exhaust duct assembly is configured to receive an engine exhaust stream and a propulsor exhaust stream, form a blended exhaust stream including both, and direct the blended exhaust stream out of the blended exhaust system through the blended exhaust outlet.

Abstract: An assembly for an aircraft powerplant includes a compressor rotor and an air system. The compressor rotor includes a plurality of compressor blades. The compressor blades are arranged circumferentially around the axis in a compressor blade array and are disposed in a flowpath. The air system includes an air source, an air injector and an air circuit fluidly coupling the air source to the air injector. The air system is configured to direct compressed air from the air source to the air injector through the air circuit. The air injector is configured to direct a stream of the compressed air into the flowpath and against one or more of the compressor blades to apply a rotational driving force onto the compressor rotor about an axis. The flowpath has a radial height at an injector location. The air injector projects a radial distance into the flowpath at the injector location.

Abstract: A gas turbine engine for an aircraft includes a jet nozzle. The jet nozzle includes an upper split duct panel and a lower split duct panel coupled with the upper split duct panel via a first overlap joint and a second overlap joint. The jet nozzle also includes at least one actuator configured to receive a command signal from a controller, and based on the command signal, reposition the upper split duct panel and lower split duct panel such that an effective area of the jet nozzle is adjusted.

Abstract: An aircraft gas turbine engine includes a fan that in operation moves air through both a core airflow path and a bypass airflow path of the gas turbine engine. The core airflow path and the bypass airflow path converge at a jet nozzle of the gas turbine engine. A method of controlling the gas turbine engine includes detecting, at a controller of the gas turbine engine, a cruise operating condition of the gas turbine engine, and in response to detecting the cruise operating condition, operating a mechanism of the gas turbine engine to decrease an effective area of the jet nozzle.

Abstract: An aircraft gas turbine engine includes a fan that in operation moves air through both a core airflow path and a bypass airflow path of the gas turbine engine. The core airflow path and the bypass airflow path converge at a jet nozzle of the gas turbine engine. A method of controlling the gas turbine engine includes detecting, at a controller of the gas turbine engine, a cruise operating condition of the gas turbine engine, and in response to detecting the cruise operating condition, repositioning a plurality of overlap jointed split duct panels such that an effective area of the jet nozzle is reduced.

Abstract: A gas turbine engine for an aircraft includes an outer bypass section wall, and a jet nozzle including at least one inflatable diaphragm. The at least one inflatable diaphragm is disposed along the outer bypass section wall. The gas turbine engine also includes a fluid pressure sensor configured to measure a fluid pressure within the at least one inflatable diaphragm, an inlet valve configured to control a pressurized flow of a fluid into the at least one inflatable diaphragm in response to a command from a controller, and a release valve configured to control a release of the fluid from within the at least one inflatable diaphragm in response to a command from the controller.

Abstract: An aircraft gas turbine engine includes an exhaust nozzle having a nozzle flowpath, and a nacelle of the gas turbine engine at least partially defining an exhaust nozzle flow area of the exhaust nozzle. The nacelle extends axially along an engine central longitudinal axis of the gas turbine engine and circumferentially around the engine central longitudinal axis. A shutter vector apparatus is attached to the nacelle and is operable between a stowed position and a deployed position. The shutter vector apparatus is configured to modulate the exhaust nozzle flow area when the shutter vector apparatus is moved between the stowed position and the deployed position. The shutter vector apparatus includes a plurality of shutter elements, each shutter element having at least one aerodynamic surface extending into the nozzle flowpath of the exhaust nozzle when the shutter vector apparatus is in the deployed position.

Abstract: An aircraft propulsion system includes an engine, an electric machine, and a gearbox. The gearbox includes an output shaft with an axis, an electric machine drive gear mounted on the output shaft and driven by the electric machine, and an engine drive gear couplable with the output shaft by a clutch assembly. The clutch assembly includes a first coupling assembly, a second coupling assembly, and a magnetic alignment system. The first coupling assembly includes a first body mounted on the engine drive gear. The second coupling assembly includes a sliding coupling housing mounted on the output shaft and movable between first and second positions. A second body is mounted on the housing. The second body is disengaged from the first in the first position and engaged in the second. The magnetic alignment system includes magnets on the bodies that couple magnetically in the second position.

Abstract: An impeller for a gas turbine engine includes an impeller hub having an impeller leading edge and an impeller trailing edge and a plurality of bifurcated impeller blades arranged on the impeller hub and extending from the impeller leading edge to the impeller trailing edge, each bifurcated impeller blade having a bifurcated pressure side and a bifurcated suction side. The bifurcated pressure side and the bifurcated suction side of each bifurcated impeller blade separate at a bifurcation point and extend to the impeller trailing edge with a reduced flow channel defined between adjacent bifurcated impeller blades. A blocked zone is defined within each bifurcated impeller blade between the bifurcated pressure side and the bifurcated suction side and each of the bifurcated pressure side and the bifurcated suction side extend tangentially from the bifurcation point at different radii of curvature.

Abstract: An assembly for a propulsion system of an aircraft includes a gearbox, at least one accessory load assembly, a propulsor, and an electric motor. The gearbox module includes a gear assembly and an output shaft. The gear assembly is connected to the output shaft. The at least one accessory load assembly includes at least one accessory load coupled to the output shaft. The propulsor is coupled to the output shaft. The electric motor includes a rotor. The rotor is coupled to the gear assembly to drive rotation of the output shaft about a rotational axis. The rotation of the output shaft drives rotation of the propulsor and the at least one accessory load for each accessory load assembly of the at least one accessory load assembly.

Abstract: An assembly for a propulsion system of an aircraft includes a gearbox module, an electric motor assembly, a first accessory load assembly, and a propulsor. The gearbox module includes a gear assembly and an output shaft. The gear assembly includes a main gear and a plurality of offset gears. The electric motor assembly includes an electric motor. The electric motor includes a rotor. The rotor is mounted to a first offset gear of the plurality of offset gears. The rotor is configured for rotation about a rotational axis to drive rotation of the gear assembly and the output shaft. The first accessory load assembly includes at least one first accessory load. The at least one first accessory load is mounted to a second offset gear of the plurality of offset gears. The propulsor is coupled to the output shaft.

Abstract: A helicopter has an air inlet barrier filter (IBF) system including a guide rail extending axially along one side of a nacelle housing a helicopter engine. A filter panel is slidable along the guide rail for movement between a filtered position in which the filter panel covers an air inlet of the nacelle and an unfiltered position in which the filter panel uncovers a total surface area of the air inlet to provide for a fully unobstructed air flow to the engine.