A method of and system for operating a hybrid-electric propulsion system is provided. The system has a thermal engine and an electrical propulsion subsystem having a plurality of components. The method includes providing a set of original engine ratings for operating the hybrid-electric propulsion system, the original engine ratings are based on one or more first performance/capability parameters of an original electrical propulsion subsystem component; replacing the original component with an alternative component, the alternative component having one or more second performance/capability parameters, wherein the second performance/capability parameters are different from the first performance/capability parameters; producing a set of alternative engine ratings based on the second performance/capability parameters; and operating the hybrid-electric propulsion system using the set of alternative engine ratings.

A vehicle includes a gas turbine engine having at least two spools and an associated power system. The power system includes two independent power subsystems, including a first power subsystem for managing power transfer between spools and a second power subsystem for supplying a base power load to the vehicle. The first power subsystem has a first electric machine mechanically coupled with a first spool of the gas turbine engine and a second electric machine mechanically coupled with a second spool. The second electric machine is electrically coupled with the first electric machine such that electrical power is transmittable therebetween. The second power subsystem has a third electric machine mechanically coupled with one of the spools. The third electric machine is electrically coupled with a load positioned offboard the gas turbine engine. The first power subsystem and the second power subsystem are electrically decoupled from one another.

A turbo-compounded engine includes a piston engine connected to drive a propulsor. An outlet of the piston engine is operable to connect products of combustion from the piston engine to pass over a turbine. The turbine is connected to drive a turbine shaft also connected to drive the propulsor. An outlet of the turbine is connected into an exhaust duct configured to exhaust the products of combustion. The exhaust duct is provided with an exhaust duct outer wall defining an exhaust chamber. A further cooling air outer wall is positioned outwardly of the exhaust duct. Flow dividers are received within an exhaust chamber inward of the exhaust duct outer wall. The exhaust duct outer wall has an inner surface and the flow dividers have an outer surface. Acoustic treatment is provided on both the inner surface of the exhaust duct outer wall and the outer surface of the flow dividers.

A power reduction system for an energy storage system of an aircraft includes a controller configured to control power reduction of power supplied from the energy storage system to an aircraft engine supply bus; and an override switch configurable in an override state and a non-override state. The override switch is configured to: in the non-override state, permit the controller to control the power reduction according to a default configuration comprising one or more parameters that trigger the power reduction; and in the override state, control the power reduction to be performed according to a relaxed configuration that at least one of relaxes and omits the one or more parameters in the default configuration.

The invention relates to a propulsion system intended to be mounted on an aircraft comprising a main body, said propulsion system comprising: a first rotating propulsive member and a second rotating propulsive member that are intended to be mounted on either side of said main body, a transmission housing connected to the first rotating propulsive member via a first mechanical shaft and to the second rotating propulsive member via a second mechanical shaft, a single gas generator connected to said transmission housing and configured to rotate the first rotating propulsive member and the second rotating propulsive member, anda single auxiliary turbomachine configured to rotate the first rotating propulsive member and the second rotating propulsive member independently of the gas generator.

An aircraft system is provided that includes a propulsor rotor, an electric machine and a gas turbine engine. The electric machine is operatively coupled to and configured to drive rotation of the propulsor rotor. The gas turbine engine is operatively coupled to and configured to drive rotation of the propulsor rotor. The gas turbine engine includes a compressor section, a combustor section, a turbine section, an exhaust duct and a flowpath extending through the compressor section, the combustor section, the turbine section and the exhaust duct. The exhaust duct extends longitudinally along the electric machine. The exhaust duct extends partially circumferentially about the electric machine between opposing circumferential sides of the exhaust duct.

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.

Propulsion engines and methods of accessing components within propulsor cavities of propulsion engines are disclosed. A propulsion engine includes an outer engine housing that includes a propulsor cavity located therein. The propulsor cavity is axially located between a low-pressure compressor and a fan of the propulsion engine. An electric converter is disposed within the propulsor cavity.

A fuel pod for a hybrid electric aircraft. The fuel pod includes a housing, a fuel tank, a generator and a connection mechanism. The fuel tank is contained within the housing and is configured to hold a fuel therein. The generator is contained within the housing and is connected to the fuel tank. The generator is configured to power at least one of a plurality of flight components of a hybrid electric aircraft. The connection mechanism is at the housing and is configured to removably attach the fuel pod to the hybrid electric aircraft. The connection mechanism includes an electrical interface configured to electrically link to at least one of the plurality of flight components of the hybrid electric aircraft, and a communication interface configured to communicatively link to a flight controller communicatively connected to the hybrid electric aircraft.

Systems, apparatuses, and methods for overcoming the disadvantages of current air transportation systems that might be used for regional travel by providing a more cost effective and convenient regional air transport system. In some embodiments, the inventive air transport system, operational methods, and associated aircraft include a highly efficient plug-in series hybrid-electric powertrain (specifically optimized for aircraft operating in regional ranges), a forward compatible, range-optimized aircraft design, enabling an earlier impact of electric-based air travel services as the overall transportation system and associated technologies are developed, and platforms for the semi-automated optimization and control of the powertrain, and for the semi-automated optimization of determining the flight path for a regional distance hybrid-electric aircraft flight.