An aircraft wing including: a wingbox; a fuel tank; a fuel cell system with a fuel cell; a fuel line configured to deliver fuel from the fuel tank to the fuel cell system; a propulsion system carried by the wingbox; and an electrical power line configured to deliver electrical power from the fuel cell system to the propulsion system. The fuel tank and the fuel cell system are located inside the wingbox, and the propulsion system is located outside the wingbox.

An aircraft wing including: a wingbox; a fuel tank; a fuel cell system with a fuel cell; a fuel line configured to deliver fuel from the fuel tank to the fuel cell system; a propulsion system carried by the wingbox; and an electrical power line configured to deliver electrical power from the fuel cell system to the propulsion system. The fuel tank and the fuel cell system are located inside the wingbox, and the propulsion system is located outside the wingbox.

Highly efficient apparatuses and systems comprise power generation systems including energy derived from an aluminum/water reactor in line with fuel cell electricity generation, with hydrogen and water produced at system stages and recirculated and re-used through the system in combination with waste heat reclamation increasing system efficiency and sustainability for powering vehicle propulsion needs.

Highly efficient apparatuses and systems comprise power generation systems including energy derived from an aluminum/water reactor in line with fuel cell electricity generation, with hydrogen and water produced at system stages and recirculated and re-used through the system in combination with waste heat reclamation increasing system efficiency and sustainability for powering vehicle propulsion needs.

An energy conversion arrangement for an aircraft, an energy system and an aircraft including an energy conversion arrangement and/or an energy system are provided. The energy conversion arrangement includes a fuel conversion device, in particular a fuel cell system, for converting at least one fuel to electrical and/or mechanical energy; an expansion device arranged in a flow path of exhausts produced in the fuel conversion device and configured to decompress the exhausts; an exhaust outlet for letting out exhausts produced in the fuel conversion device by the fuel conversion; and at least one bypass duct configured to allow the exhausts to bypass the expansion device on their way from the fuel conversion device to the exhaust outlet.

A flying vehicle propulsion system comprises a propulsor, a drive system, a heat exchanger, and a housing in which the heat exchanger is provided. The propulsor produces a propulsor fluid flow. In a first operation configuration of the propulsion system, at least part of the propulsor fluid flow is incident on the exchanger. A propulsor fluid flow inlet port of the housing fluidly communicates with a chamber of the housing on an inlet side of the exchanger. The inlet port receives the propulsor fluid flow for ingestion into the chamber and exchanger and comprises a valve to close the port when the valve is closed and open the port when the valve is open. The valve is biased such that at least one of: the valve opens passively under a propulsor fluid flow rate influence above a pre-defined threshold impinging on the valve; and the valve closes passively under a biasing influence.

A flying vehicle propulsion system comprises a propulsor, a drive system, a heat exchanger, and a housing in which the heat exchanger is provided. The propulsor produces a propulsor fluid flow. In a first operation configuration of the propulsion system, at least part of the propulsor fluid flow is incident on the exchanger. A propulsor fluid flow inlet port of the housing fluidly communicates with a chamber of the housing on an inlet side of the exchanger. The inlet port receives the propulsor fluid flow for ingestion into the chamber and exchanger and comprises a valve to close the port when the valve is closed and open the port when the valve is open. The valve is biased such that at least one of: the valve opens passively under a propulsor fluid flow rate influence above a pre-defined threshold impinging on the valve; and the valve closes passively under a biasing influence.

An aircraft power plant, has: an air mover for propelling an aircraft; an electric motor drivingly engaged with the air mover; a gas turbine engine having a compressor for pressurizing air, a combustor in which the pressurised air is mixed with fuel and ignited for generating combustion gases, and a turbine for extracting energy from the combustion gases; and a hydrogen fuel cell operatively connected to the electric motor for powering the electric motor with electricity generated by the hydrogen fuel cell, the hydrogen fuel cell operable to generate electricity using the air from the compressor and hydrogen from a source of hydrogen.

An aircraft power plant, has: an air mover for propelling an aircraft; an electric motor drivingly engaged with the air mover; a gas turbine engine having a compressor for pressurizing air, a combustor in which the pressurised air is mixed with fuel and ignited for generating combustion gases, and a turbine for extracting energy from the combustion gases; and a hydrogen fuel cell operatively connected to the electric motor for powering the electric motor with electricity generated by the hydrogen fuel cell, the hydrogen fuel cell operable to generate electricity using the air from the compressor and hydrogen from a source of hydrogen.

A power generation system for an aircraft includes: a storage tank for storing hydrogen; a fuel cell configured to generate power from the hydrogen; a fuel supply line configured to supply the hydrogen from storage tank to the fuel cell; a fresh air supply line configured to supply air to a cabin air supply system; and a fuel-air heat exchange system, wherein the fuel supply line and the air supply line pass through the fuel-air heat exchange system such that the hydrogen cools the air in use.