Abstract: An aircraft powerplant includes an engine having an output power shaft. The aircraft powerplant further includes a power transmission coupled to the output power shaft of the engine. The power transmission is configured to divide power output of the engine between a mechanical power output and an electrical power output. A majority of the power output from the engine is adjustable to output to either of the mechanical power output or the electrical power output. The aircraft powerplant further includes a propulsion mechanism coupled to the mechanical power output. The aircraft powerplant further includes a control system configured to cause the power transmission to deliver the majority of the power output of the engine to the propulsion mechanism to generate thrust or deliver the majority of the power output of the engine as electrical power output via the electrical power output.

Abstract: An enclosure for an aircraft powerplant includes an air inlet, an air outlet, and at least one sidewall forming the enclosure and fluidly connecting the air inlet and the air outlet. The enclosure further includes a cavity configured to house at least one component of the aircraft powerplant. The cavity is within the enclosure and formed by the at least one sidewall. The enclosure further includes a noise reduction chamber comprising a plurality of channels configured to permit air to pass through the noise reduction chamber.

Abstract: A hybrid aircraft powerplant includes a turbine engine having a first shaft configured to output power from the turbine engine, a bypass fan, and an electric machine. The hybrid aircraft powerplant further includes a first mechanism configured to selectively engage the first shaft with a second shaft connected to the electric machine such that the power is output from the turbine engine to the electric machine. The hybrid aircraft powerplant further includes a second mechanism configured to selectively engage the first shaft with a third shaft connected to the bypass fan to output the power from the turbine engine to the bypass fan.

Abstract: A turbocharger includes a compressor configured to compress intake air for an engine. The turbocharger further includes an electric motor configured to power the compressor. The turbocharger further includes a turbine configured to receive exhaust air from the engine. The turbocharger further includes an electric generator configured to be driven by the turbine to generate electric power.

Abstract: A lever for adjusting output of a hybrid-electric powerplant of an aircraft includes a lever configured to move over an overall range of positions. Movement of the lever adjusts the output of the hybrid-electric powerplant between at least two modes of operation. In a first subset of positions within the overall range of positions, the hybrid electric powerplant is configured to operate an engine having a mechanical output, output first electrical energy from a motor/generator driven by the mechanical output of the engine, and drive a propulsion mechanism by the mechanical output of the engine. In a second subset of positions within the overall range of positions, the hybrid electric powerplant is configured to operate the engine having the mechanical output, receive second electrical energy at the motor/generator, drive the mechanical output with the motor/generator using the second electrical energy, and drive the propulsion mechanism by the mechanical output.

Abstract: An aerospace hybrid powertrain system includes an engine, a power shaft, and an electric machine having the power shaft therein or passing therethrough. The aerospace hybrid powertrain system further includes a fan, impeller, or blower connected to the power shaft and configured to direct air toward components of at least one of the engine or the electric machine. The fan, impeller, or blower may further be configured to direct air toward cooling elements such as heat exchangers or finned heat sinks arranged to cool the components of at least one of the piston combustion engine or the electric machine.

Abstract: An energy source for an aircraft includes an enclosure, an engine, an electric generator, and at least one fuel tank configured to provide fuel to the engine; and electrical connectors for outputting power generated by the electric generator to at least one electrical component or electrical bus of the aircraft. The engine, the electric generator, and the at least one fuel tank are each housed within the enclosure.

Abstract: A hybrid powertrain system includes an engine, an electric machine having a power shaft therein, and a clutch configured to releasably engage an output of the engine and the power shaft of the electric machine. The electric machine further includes an electrical output. The power shaft is configured to mechanically attach to and provide mechanical power to a propulsion device. A controller is configured to control the engine, the electric machine, and the clutch to implement one or more power output modes.