A fuel system is provided for an aircraft having a fuel source. The fuel system includes a fuel oxygen reduction unit defining a liquid fuel supply path, a stripping gas supply path, a liquid fuel outlet path, and a stripping gas return path, wherein the stripping gas return path is in airflow communication with the fuel source.

A fuel system is provided for an aircraft having a fuel source. The fuel system includes a fuel oxygen reduction unit defining a liquid fuel supply path, a stripping gas supply path, a liquid fuel outlet path, and a stripping gas return path, wherein the stripping gas return path is in airflow communication with the fuel source.

A device and a method for improving combustion are disclosed. In an embodiment the device includes a combustion chamber including at least one combustion chamber inlet for feeding in fuel or air or the fuel/air mixture, a reactor chamber connected upstream of the combustion chamber, the reactor chamber comprising a plasma generator, wherein the plasma generator is a piezoelectric transformer configured to operate with a low voltage and a control apparatus for the plasma generator, wherein the device is configured in such a way that even before a start of an actual combustion process at least one gaseous component in the reactor chamber is enriched with radicals and ions by the plasma generator.

A device and a method for improving combustion are disclosed. In an embodiment the device includes a combustion chamber including at least one combustion chamber inlet for feeding in fuel or air or the fuel/air mixture, a reactor chamber connected upstream of the combustion chamber, the reactor chamber comprising a plasma generator, wherein the plasma generator is a piezoelectric transformer configured to operate with a low voltage and a control apparatus for the plasma generator, wherein the device is configured in such a way that even before a start of an actual combustion process at least one gaseous component in the reactor chamber is enriched with radicals and ions by the plasma generator.

The present invention is a fluids mechanical system for optimizing the catalytic effect of catalytic alloys for the elimination of microbiological contaminants in hydrocarbon fuels, that has catalytic alloy pieces mainly formed of tin and antimony, which are contained in a container that can be a metal tube, a stainless steel mesh or another type of plastic container, characterized in that the volume of the pieces or pellets of catalytic alloy is less than 60 cubic millimeters, preferably between 10 cubic millimeters and 45 cubic millimeters, the pieces having a spherical, disc or irregular shape.

A gas removal unit has a tube bundle formed of a plurality of tubes with a hollow center. The tubes are formed of a material that allows passage of a gas from an exterior of the tube into an interior of the tube and resists flow of at least some liquids through the tube into the interior of the tube. There is a plurality of inner chambers within the bundle and a plurality of outer chambers outward of the bundle. A fluid inlet connects to a first of the inner or outer chambers and a fluid outlet connects to a second of the inner and outer chambers. An axial direction is defined between the fluid inlet to the fluid outlet. A tortuous path is defined by the inner and outer chambers such that a fluid will pass repeatedly from the inner chambers to the outer chambers, and from the outer chambers to the inner chambers, as it moves along the axial direction from the fluid inlet to the fluid outlet. A fuel supply system is also disclosed.

A chemical scavenging component includes a porous body that has a radical-scavenging material. The radical-scavenging material has a composition of, by weight, greater than 50% of cerium oxide that is chemically active with regard to oxygen-containing radicals.

A chemical scavenging component includes a porous body that has a radical-scavenging material. The radical-scavenging material has a composition of, by weight, greater than 50% of cerium oxide that is chemically active with regard to oxygen-containing radicals.

A method of operating a gas turbine engine having a lean burn staged combustion system having a combustor in which fuel is combusted. The gas turbine engine includes a fuel-oil heat exchanger arranged to transfer heat between oil and fuel that is provided to the combustor. The method includes transferring heat from the oil to the fuel before the fuel enters the combustor so as to lower the fuel viscosity to 0.58 mm.sup.2/s or lower on entry to the combustor at cruise conditions.

There is provided a method of operating a gas turbine engine. The gas turbine engine comprises a staged combustor having an arrangement of fuel spray nozzles in which fuel flow is biased to a subset of the nozzles adjacent one or more ignitors during a re-light procedure. The method comprises transferring heat from the oil to the fuel before the fuel enters the combustor so as to lower the fuel viscosity to 0.58 mm.sup.2/s or lower on entry to the combustor at cruise conditions. Also disclosed is a gas turbine engine.