Abstract: The present disclosure relates generally to a system for inerting a fuel tank. The system includes a fuel pump, a jet ejector, a first flow path between the fuel pump and the jet ejector, a valve along the first flow path, the valve blocking the fuel flow from the fuel pump to the jet ejector when closed, a second flow path from the ullage of the fuel tank to the jet ejector to allow fuel vapor from the ullage to travel from the ullage to the jet ejector, a vaporizer downstream of the jet ejector and configured to vaporize the fuel received from the jet ejector into the fuel vapor, and a third flow path along which the fuel vapor flows from the vaporizer to the ullage so that an fuel-air ratio in the ullage of the fuel tank is maintained at greater than a flammable fuel-air ratio.

Abstract: The present disclosure relates generally to a system for removing fuel from a mixture of air and fuel vapor in an ullage space of an aircraft fuel tank. The system includes a compressor for drawing the mixture of air and fuel vapor from the ullage space and directing the mixture of air and fuel vapor through a heat exchanger where the mixture of air and fuel vapor is cooled. The system also includes a turbine configured to be driven by the mixture of air and fuel from the heat exchanger. Power from the turbine can be transferred back toward the compressor to assist in driving rotation of the compressor. The system further includes a separator for receiving the mixture of air and fuel vapor from the turbine and separating at least some liquid fuel from the mixture of air and fuel vapor. From the separator, a separated liquid fuel and a mixture of air and fuel vapor with reduced concentration of fuel vapor are returned to the aircraft fuel tank.

Abstract: An aircraft fuel tank inerting system for a fixed wing aircraft having at least one main fuel tank in the wing and an associated surge tank includes a source of inerting fluid and a flow passage for supplying said inerting fluid to the main fuel tank and discharging it into the main filet tank through at least one discharge outlet. The flow passage includes a pressure relief arrangement adapted to discharge into the surge tank if a pressure in the main fuel tank exceeds a predetermined threshold.

Abstract: An aircraft fuel tank inerting system for a fixed wing aircraft having at least one main fuel tank in the wing and an associated surge tank includes a source of inerting fluid and a flow passage for supplying said inerting fluid to the main fuel tank and discharging it into the main filet tank through at least one discharge outlet. The flow passage includes a pressure relief arrangement adapted to discharge into the surge tank if a pressure in the main fuel tank exceeds a predetermined threshold.