An integrated fuel and environmental control system is provided and includes a first heat exchanger in which fuel and oil thermally communicate and a second heat exchanger disposable in a super-cooled fluid flow. The second heat exchanger is receptive of at least one of the fuel and oil from the first heat exchanger whereby the at least one of the fuel and oil thermally communicate with the super-cooled fluid flow. The second heat exchanger is also receptive of a second fluid whereby the second fluid thermally communicates with the super-cooled fluid flow downstream from the thermal communication of the super-cooled fluid flow with the at least one of the fuel and oil.

An electronics cooling system for an aircraft includes a heat exchanger comprising a coolant circuit, an air circuit, and a fuel circuit such that each of the circuits is in thermal communication with at least one of the other circuits. The coolant circuit is in thermal communication with one or more aircraft electronics. The air circuit is in fluid communication with at least one air source. The fuel circuit is in fluid communication with a fuel tank between the fuel tank and an engine of the aircraft.

A gas inerting system for an aircraft includes a fuel tank configured to contain a liquid fuel, a fuel vaporization system in fluid communication with the fuel tank and configured to receive the liquid fuel from the fuel tank, a source of air in fluid communication with the fuel vaporization system and configured to deliver air into the liquid fuel to produce the fuel vapor, a heat exchanger in fluid communication with the source of air at a location upstream of the fuel vaporization system, and a catalytic oxidation unit in fluid communication with the fuel vaporization system. The heat exchanger is configured to cool the air from the air source. A fluid connection is configured to deliver the fuel vapor to the catalytic oxidation unit.

A cryogenic cooling system for an aircraft includes a first air cycle machine, a second air cycle machine, and a means for collecting liquid air. The first air cycle machine is operable to output a cooling air stream based on a first air source. The second air cycle machine is operable to output a chilled air stream at a cryogenic temperature based on a second air source cooled by the cooling air stream of the first air cycle machine. An output of the second air cycle machine is provided to the means for collecting liquid air.

A system for an aircraft includes an engine bleed source of a gas turbine engine. The system also includes a means for chilling an engine bleed air flow from the engine bleed source to produce a chilled working fluid. The system further includes a means for providing the chilled working fluid for an aircraft use.

A propulsion system includes an electric fan propulsion motor with a plurality of propulsion motor windings. The propulsion system also includes a means for controlling a flow rate of a working fluid through a cryogenic working fluid flow control assembly to the propulsion motor windings.

An aircraft inert gas generating system includes a fuel source configured to supply fuel, a stream of reaction air having a first temperature, an air-fuel mixing unit configured to receive an amount of the fuel and an amount of the reaction air stream to create an air-fuel mixture, and a catalytic oxidation unit configured to receive and react the air-fuel mixture. The stream of reaction air includes an amount of mixing air from a mixing air source, and the mixing air source includes a primary heat exchanger of an aircraft ram circuit and a cooling air extraction element proximate the heat exchanger. The mixing air can alternatively include cool air from a heat sink air source.

A cooling system in which an ACS (air cycle system) turbine may be driven by high pressure air from a turbo-fan engine and a VCS (vapor cycle system) having an evaporator and a VCS refrigerant compressor may be driven by the ACS turbine. Fluid of the chilled fluid reservoir, which may be chilled fuel, may be circulated through and cooled in the evaporator. In some embodiments, the ACS turbine may be coupled to the VCS refrigerant compressor by a magnetic coupling.

A method of conditioning oxygen depleted air (ODA) exhausted from a fuel cell comprising the steps of; taking fuel from an aircraft fuel tank collector cell, delivering said fuel to a rear mounted engine via a primary heat exchanger, taking exhaust ODA from a fuel cell, passing the ODA through the primary heat exchanger in the opposite direction to the fuel, such that the fuel acts as a heat sink for the ODA, to cool the ODA, passing the ODA through a dryer, to dry the ODA and using the cooled, dried ODA to inert fuel in the aircraft fuel tank.

A fuel tank inerting system includes a cabin air source, a conduit, a heat exchanger, and a pressurized air source. In embodiments, the pressurized air source is configured to provide pressurized air to the heat exchanger, and the conduit is configured to provide cabin air from the cabin air source to the heat exchanger.