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 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 scramjet includes a converging inlet, a combustor configured to introduce a fuel stream into an air stream in a combustion chamber and to combust the fuel air mixture stream to create an exhaust stream, and a diverging exit nozzle configured to accelerate the exhaust stream. The combustor includes a fuel injection system including at least one arcjet. A method of creating thrust for an aircraft includes compressing a supersonic incoming air stream in a converging inlet, injecting a fuel stream into the air stream in a combustion chamber to create a fuel air mixture stream, igniting the fuel air mixture stream to create an exhaust stream, and exhausting the exhaust stream from a diverging exit nozzle. The injecting the fuel stream into the air stream includes injecting the fuel stream at a fuel speed sufficient to create shear between the fuel stream and the air stream.

A scramjet includes a converging inlet, a combustor configured to introduce a fuel stream into an air stream in a combustion chamber and to combust the fuel air mixture stream to create an exhaust stream, and a diverging exit nozzle configured to accelerate the exhaust stream. The combustor includes a fuel injection system including at least one arcjet. A method of creating thrust for an aircraft includes compressing a supersonic incoming air stream in a converging inlet, injecting a fuel stream into the air stream in a combustion chamber to create a fuel air mixture stream, igniting the fuel air mixture stream to create an exhaust stream, and exhausting the exhaust stream from a diverging exit nozzle. The injecting the fuel stream into the air stream includes injecting the fuel stream at a fuel speed sufficient to create shear between the fuel stream and the air stream.

A nozzle includes an outer gas flow path, an inner gas flow path radially inward from the outer gas flow path, a liquid flow path defined radially between the inner gas flow path and the outer gas flow path, and a core conduit defined radially inward from the inner gas flow path. An injector assembly includes an outer housing, a nozzle within the outer housing, and an outer housing gas flow path defined radially outward from the nozzle between an inner surface of the outer housing and an outer surface of the nozzle. The nozzle includes an outer gas flow path, an inner gas flow path radially inward from the outer gas flow path, a liquid flow path defined radially between the inner gas flow path and the outer gas flow path and a core conduit defined radially inward from the inner gas flow path.

A nozzle includes an outer gas flow path, an inner gas flow path radially inward from the outer gas flow path, a liquid flow path defined radially between the inner gas flow path and the outer air flow path, and a core conduit defined radially inward from the inner gas flow path. An injector assembly includes an outer housing, a nozzle within the outer housing, and an outer housing gas flow path defined radially outward from the nozzle between an inner surface of the outer housing and an outer surface of the nozzle. The nozzle includes an outer gas flow path, an inner gas flow path radially inward from the outer gas flow path, a liquid flow path defined radially between the inner gas flow path and the outer gas flow path and a core conduit defined radially inward from the inner gas flow path.

A fuel treatment system for effecting reduced emissions when combusting the fuel comprises a fuel treatment device comprising an inlet connectable to a main fuel tank and an outlet for supplying treated fuel. The fuel treatment device comprises a treatment section between said inlet and outlet, and a pump for pumping the fuel from said inlet through the treatment section to said outlet. A manifold device has an inlet connected to the outlet of the fuel treatment device, and a first outlet connectable to a fuel consumption device for supplying the treated fuel thereto. A first recirculation line connects a second outlet of the manifold device and the inlet of the fuel treatment device for recirculating treated fuel from the manifold device to the fuel treatment device.

A fuel treatment system for effecting reduced emissions when combusting the fuel comprises a fuel treatment device comprising an inlet connectable to a main fuel tank and an outlet for supplying treated fuel. The fuel treatment device comprises a treatment section between said inlet and outlet, and a pump for pumping the fuel from said inlet through the treatment section to said outlet. A manifold device has an inlet connected to the outlet of the fuel treatment device, and a first outlet connectable to a fuel consumption device for supplying the treated fuel thereto. A first recirculation line connects a second outlet of the manifold device and the inlet of the fuel treatment device for recirculating treated fuel from the manifold device to the fuel treatment device.

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 gas-fired burner adapted for use on a liquid fuel. A method for essentially smokeless start-up and steady state operation of a gas-fired burner on a liquid fuel. The apparatus integrates a catalytic liquid fuel reformer with a flame burner designed for operation on a gaseous fuel of high Wobbe Index, e.g., natural gas. The method involves reacting a mixture of a liquid fuel and oxidant in a catalytic reformer to obtain a gaseous reformate having a low Wobbe Index; and thereafter combusting the gaseous reformate, optionally augmented with liquid co-fuel and oxidant, in the gas-fired burner under diffusion flame conditions. The invention allows commercial gas-fired appliances to be operated on a liquid fuel, thereby offering advantages in logistics and camp operations.