Aircraft fuel ice capturing filter device housings, aircraft fuel ice capturing filter devices, and methods of use are provided.

A fuel freeze mitigation and/or prevention system includes a power generator configured and adapted to be positioned within a fuel storage tank. A fluid mover device is in electrical communication with the power generator. The fluid mover device is configured and adapted to be positioned within a fuel storage tank to mitigate or prevent fuel freeze in the fuel storage tank. A method for mitigating or preventing fuel freeze in a fuel storage tank includes harvesting energy with a power generator positioned within the fuel storage tank, charging a battery with the harvested energy, monitoring a fuel temperature inside the fuel storage tank, and turning a fluid mover device positioned within the fuel storage tank ON or OFF depending on at least one of a manual command or the fuel temperature inside the fuel storage tank to mitigate or prevent fuel freeze in the fuel storage tank.

Disclosed are systems and methods for maintaining bulk fuel temperatures in an aircraft. In one aspect, a recirculation system causes fuel to be delivered from a relatively low point near the feed hopper of each tank on the aircraft to one or more outboard locations of the wings. Once there, the fuel, due to gravity, flows back over the lower skin of the wing in channels back towards the fuselage, thus cooling the fuel. In other aspects, control systems are disclosed that coordinate the recirculation based on fuel levels in the tanks and fuel temperatures. The control systems also utilize a fuel scavenge system to maintain acceptable temperatures in the tanks.

Disclosed are systems and methods for maintaining bulk fuel temperatures in an aircraft. In one aspect, a recirculation system causes fuel to be delivered from a relatively low point near the feed hopper of each tank on the aircraft to one or more outboard locations of the wings. Once there, the fuel, due to gravity, flows back over the lower skin of the wing in channels back towards the fuselage, thus cooling the fuel. In other aspects, control systems are disclosed that coordinate the recirculation based on fuel levels in the tanks and fuel temperatures. The control systems also utilize a fuel scavenge system to maintain acceptable temperatures in the tanks.

A system for energy conversion that includes a propulsion system, a fuel circuit, a combustion device, a turbine, and a load device. The fuel circuit is in fluid communication with a fuel tank and a fuel flow control device that separates a flow of fuel into a first portion and a second portion. The combustion device receives a flow of oxidizer and the second portion of fuel to generate combustion gases. The turbine receives the combustion gases from the combustion device via a fluid circuit. The load device is operably coupled to the turbine via a driveshaft and is configured to receive torque from the driveshaft.

A system for energy conversion that includes a propulsion system, a fuel circuit, a combustion device, a turbine, and a load device. The fuel circuit is in fluid communication with a fuel tank and a fuel flow control device that separates a flow of fuel into a first portion and a second portion. The combustion device receives a flow of oxidizer and the second portion of fuel to generate combustion gases. The turbine receives the combustion gases from the combustion device via a fluid circuit. The load device is operably coupled to the turbine via a driveshaft and is configured to receive torque from the driveshaft.

A fluid distribution system includes a boost supply providing a fluid flow, and a fluid metering system downstream of the boost supply. The fluid metering system supplies fluid to a downstream device. A main fluid pump supplies at least a portion of the fluid flow to the fluid metering system. A shut-off valve is positioned upstream of a main fluid pump inlet. An actuation system is positioned downstream of the boost supply. The actuation system supplies fluid to one or more hydraulically-operated devices. An actuation pump supplies at least a portion of the fluid flow to the fluid metering system and to the actuation system. A first valve is positioned between the actuation pump and the fluid metering system. The first valve and the shut-off valve are operable to switch between the main fluid pump and the actuation pump as a source of fluid supply to the fluid metering system.

A fluid distribution system includes a boost supply providing a fluid flow, and a fluid metering system downstream of the boost supply. The fluid metering system supplies fluid to a downstream device. A main fluid pump supplies at least a portion of the fluid flow to the fluid metering system. A shut-off valve is positioned upstream of a main fluid pump inlet. An actuation system is positioned downstream of the boost supply. The actuation system supplies fluid to one or more hydraulically-operated devices. An actuation pump supplies at least a portion of the fluid flow to the fluid metering system and to the actuation system. A first valve is positioned between the actuation pump and the fluid metering system. The first valve and the shut-off valve are operable to switch between the main fluid pump and the actuation pump as a source of fluid supply to the fluid metering system.

An aircraft fuel deoxygenation system includes a boost pump, a contactor-separator, and a centrifuge-separator pump. The boost pump is adapted to receive fuel from a fuel source and inert gas from an inert gas source, and is configured to mix the fuel and inert gas and supply a fuel/gas mixture. The contactor-separator is coupled to receive the fuel/gas mixture and is configured to remove oxygen from the fuel and thereby generate and supply deoxygenated fuel with entrained purge gas and separated purge gas. The centrifuge-separator pump is coupled to receive the deoxygenated fuel with entrained purge gas and is configured to separate and remove the entrained purge gas from the deoxygenated fuel and supply the deoxygenated fuel and additional purge gas.

An aircraft fuel deoxygenation system includes a boost pump, a contactor-separator, and a centrifuge-separator pump. The boost pump is adapted to receive fuel from a fuel source and inert gas from an inert gas source, and is configured to mix the fuel and inert gas and supply a fuel/gas mixture. The contactor-separator is coupled to receive the fuel/gas mixture and is configured to remove oxygen from the fuel and thereby generate and supply deoxygenated fuel with entrained purge gas and separated purge gas. The centrifuge-separator pump is coupled to receive the deoxygenated fuel with entrained purge gas and is configured to separate and remove the entrained purge gas from the deoxygenated fuel and supply the deoxygenated fuel and additional purge gas.