A fuel delivery system for a gas turbine engine includes a fuel tank; a draw pump downstream of the fuel tank for generating a liquid fuel flow from the fuel tank; a main fuel pump downstream of the draw pump; and a fuel oxygen conversion unit downstream of the draw pump and upstream of the main fuel pump. The fuel oxygen conversion unit includes a stripping gas line; a contactor in fluid communication with the stripping gas line and the draw pump for forming a fuel/gas mixture; and a dual separator pump in fluid communication with the contactor for receiving the fuel/gas mixture and separating the fuel/gas mixture into a stripping gas flow and the liquid fuel flow at a location upstream of the main fuel pump.

A specially designed rotary actuator comprising a sealed container and a piston rotor located in the sealed container. The piston rotor divides the sealed container into a first space and a second space having different pressures. The first end of the piston rotor faces the first space and includes a plurality of first bores, and the second end of the piston rotor faces the second space and includes a plurality of second bores. The depth of the first and second bores is less than the thickness of the piston rotor. Each of the first and second bores comprises a first portion and a second portion, wherein the surface area of the first portion is greater than the surface area of the second portion.

A specially designed rotary actuator comprising a sealed container and a piston rotor located in the sealed container. The piston rotor divides the sealed container into a first space and a second space having different pressures. The first end of the piston rotor faces the first space and includes a plurality of first bores, and the second end of the piston rotor faces the second space and includes a plurality of second bores. The depth of the first and second bores is less than the thickness of the piston rotor. Each of the first and second bores comprises a first portion and a second portion, wherein the surface area of the first portion is greater than the surface area of the second portion.

A device for regulating the fuel supply flow rate for a turbine engine, comprising at least a pump, an upstream line leading to the pump, a downstream line downstream of the pump, a recirculation duct branched off the downstream line, allowing to collect the fluid in the downstream line and channel it towards the upstream line, a means for regulating the flow rate disposed on the recirculation duct, a phase measurer disposed in the upstream line, a computing unit connected to the phase measurer and to the flow rate regulating means, said computing unit controlling the flow rate regulating means such as to control the degree of opening of said flow rate regulating means, according to the gas content value in the upstream line.

A gas turbine engine includes a first shaft coupled to a first turbine and a first compressor, a second shaft coupled to a second turbine and a second compressor, and a third shaft coupled to a third turbine and a fan assembly. The turbine engine includes a heat rejection heat exchanger configured to reject heat from a closed loop system with air passed from the fan assembly, and a combustor positioned to receive compressed air from the second compressor as a core stream. The closed-loop system includes the first, second, and third turbines and the first compressor and receives energy input from the combustor.

A fuel delivery system for a gas turbine engine includes a fuel tank; a draw pump downstream of the fuel tank for generating a liquid fuel flow from the fuel tank; a main fuel pump downstream of the draw pump; and a fuel oxygen conversion unit downstream of the draw pump and upstream of the main fuel pump. The fuel oxygen conversion unit includes a stripping gas line; a contactor in fluid communication with the stripping gas line and the draw pump for forming a fuel/gas mixture; and a dual separator pump in fluid communication with the contactor for receiving the fuel/gas mixture and separating the fuel/gas mixture into a stripping gas flow and the liquid fuel flow at a location upstream of the main fuel pump.

A fuel oxygen conversion unit includes a contactor; a fuel gas separator, the fuel oxygen conversion unit defining a circulation gas flowpath from the fuel gas separator to the contactor; and an isolation valve in airflow communication with the circulation gas flowpath for modulating a gas flow through the circulation gas flowpath to the contactor.

An engine includes a stripping gas source, a combustion section, and a fuel oxygen conversion unit positioned upstream of the combustion section, the fuel oxygen conversion unit defining a stripping gas flowpath in airflow communication with the stripping gas source. The fuel oxygen conversion unit includes a contactor defining a fuel inlet, a gas inlet in airflow communication with the stripping gas flowpath, and a fuel gas mixture outlet; and a fuel gas separator defining a fuel gas mixture inlet for receiving a fuel gas mixture from the contactor, a liquid fuel outlet, and a stripping gas outlet; wherein the stripping gas flowpath receives substantially all of a stripping gas flow therethrough from the stripping gas source and provides the stripping gas flow to the contactor.

A fuel system for an aircraft includes a fuel source and 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 and stripping gas supply path are each in airflow communication with the fuel source.

A method of operating a fuel oxygen reduction unit for a vehicle or a gas turbine engine of the vehicle is provided. The fuel oxygen reduction unit including a contactor and a fuel gas separator, and further defining a stripping gas flowpath in flow communication with a stripping gas inlet of the contactor and a stripping gas outlet of the fuel gas separator. The method includes receiving data indicative of a parameter of a stripping gas flow through the stripping gas flowpath or of a component in flow communication with the stripping gas flow through the stripping gas flowpath; and determining an operability condition of the fuel oxygen reduction unit, or a component operable with the fuel oxygen reduction unit, based on the data received indicative of the parameter of the stripping gas flow or of the component in flow communication with the stripping gas flow.