Abstract: 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.

Abstract: A mask interface for a respiratory mask, in which the mask interface comprises a resilient mask housing at least partially formed from a textile and being configured to deform under pressure from an external force, such as when being pressed against a pillow, and to substantially return to its original shape either automatically or by manipulation by a user.

Abstract: In one exemplary embodiment of the present disclosure, a method of operating a fuel system for an aeronautical gas turbine engine is provided. The method includes: providing a flow of fuel to a fuel nozzle of the aeronautical gas turbine engine during a wind down condition; operating a fuel oxygen reduction unit to reduce an oxygen content of the flow of fuel provided to the fuel nozzle of the aeronautical gas turbine engine during the wind down condition; and ceasing providing the flow of fuel to the fuel nozzle of the aeronautical gas turbine engine, the fuel nozzle comprising a volume of fuel after ceasing providing the flow of fuel to the fuel nozzle; wherein operating the fuel oxygen reduction unit comprises operating the fuel oxygen reduction unit to reduce an oxygen content of the volume of fuel in the fuel nozzle to less than 20 parts per million.

Abstract: 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.

Abstract: A wash system for a gas turbine engine includes a core turning assembly having a motor configured to be mechanically coupled to the gas turbine engine. The rotor of the core turning assembly is further configured to rotate one or more components of a compressor section or a turbine section of the gas turbine engine at a rotational speed greater than two (2) revolutions per minute and less than five hundred (500) revolutions per minute during washing operations of the gas turbine engine.

Abstract: An explosive threat mitigation unit (TMU) stands ready to receive a suspected bomb, enclose it, and contain the explosion if one occurs. An operator protects bystanders and surroundings by putting the suspected bomb in a TMU and then closing the TMU. If the bomb goes off, the TMU mitigates the effects of both the blast and the fragments. One variation has a container, a tube, a cap, and a door. The container includes an opening. The tube, arranged in the container, aligns with the opening. The cap slides through the opening and over the tube. The door slides into place to close the opening and enclose the cap within the container.

Abstract: A heat exchanger can be configured to utilize multiple sections of hardway fins that can be configured so that an upper first section of the fins can build up liquid head and a second lower section of the fins can be configured to distribute liquid in an even, or uniform, manner. The first section of fins can utilize a different type of hole arrangement than the second section of fins. For instance, the diameter or width of the holes in the first section may differ from the diameter or width of the holes of the second section. In addition (or as an alternative), fin frequency and/or spacing between immediately adjacent holes in the first section of fins may be different from the spacing between immediately adjacent holes in the second section of fins.

Abstract: A turbine engine that includes an engine core, an inner cowl, an outer cowl and an accessory gearbox. The engine core includes at least a compressor section, a combustion section, and a turbine section in axial flow arrangement. The accessory gearbox is operably coupled to the engine core and includes a first portion and a second portion.

Abstract: The present invention is a method for producing allograft tissue by applying an antimicrobial solution to allograft tissue. The antimicrobial solution exhibits antimicrobial activity to make allograft resistant to microbial organisms, such as a bacterium.

Abstract: A plug and play avionics kit includes an avionics panel, the avionics panel including avionics including instrument cluster electronics, one or more aircraft engine electrical component connections, one or more line replaceable units and one or more electrical harnesses, wherein the avionics kit is configured to install in a home build aircraft and the instrument cluster electronics, one or more engine electrical components, and one or more line replaceable units are connected by the electrical harness. The avionics panel may further include an avionics tray and a rack for line replaceable units.

Abstract: A fuel oxygen conversion unit includes a contactor defining a liquid fuel inlet, a stripping gas inlet and a fuel/gas mixture outlet; and a fuel gas separator defining a fuel/gas mixture inlet in flow communication with the fuel/gas mixture outlet of the contactor and an axis. The fuel gas separator further includes a stationary casing; and a separator assembly including a core and a plurality of paddles extending from the core, the separator assembly rotatable about the axis within the stationary casing to separate a fuel/gas mixture received through the fuel/gas mixture inlet into a liquid fuel flow and stripping gas flow.

Abstract: 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.

Abstract: An explosive threat mitigation unit (TMU) stands ready to receive a suspected bomb, enclose it, and contain the explosion if one occurs. An operator protects bystanders and surroundings by putting the suspected bomb in a TMU and then closing the TMU. If the bomb goes off, the TMU mitigates the effects of both the blast and the fragments. One variation has a container, a tube, a cap, and a door. The container includes an opening. The tube, arranged in the container, aligns with the opening. The cap slides through the opening and over the tube. The door slides into place to close the opening and enclose the cap within the container.

Abstract: A fuel oxygen reduction unit for an engine is provided. The fuel oxygen reduction unit includes a contactor including a fuel inlet that receives an inlet fuel flow and a stripping gas inlet that receives an inlet stripping gas flow, the contactor configured to form a fuel/gas mixture; a separator that receives the fuel/gas mixture, the fuel oxygen reduction unit defining a circulation gas flowpath from the separator to the contactor; and a stripping gas source selectively in fluid communication with the circulation gas flowpath for selectively introducing a stripping gas from the stripping gas source to the circulation gas flowpath, wherein the stripping gas source is an accessory gearbox.

Abstract: A fuel oxygen reduction unit assembly for a fuel system is provided. The fuel oxygen reduction unit assembly includes: a fuel oxygen reduction unit located downstream from the fuel source and defining a stripping gas flowpath and a liquid fuel flowpath, the fuel oxygen reduction unit comprising a means for transferring an amount of oxygen from a liquid fuel flow through the liquid fuel flowpath to a gas flow through the stripping gas flowpath; and an oxygen conversion unit in flow communication with the stripping gas flowpath configured to extract a flow of oxygen from a gas flow through the stripping gas flowpath, the oxygen conversion unit defining an oxygen outlet configured to provide the extracted flow of oxygen to an external system.

Abstract: A fuel delivery system for a gas turbine engine including a fuel oxygen reduction unit is provided. The fuel oxygen reduction unit defines a liquid fuel flowpath and a stripping gas flowpath and is configured to transfer an oxygen content of a fuel flow through the liquid fuel flowpath to a stripping gas flow through the stripping gas flowpath. The fuel oxygen reduction unit includes an impeller in airflow communication with the stripping gas flowpath for circulating the stripping gas flow through the stripping gas flowpath; and a turbine coupled to the impeller.

Abstract: A fuel delivery system for a gas turbine engine includes a fuel source; a draw pump downstream of the fuel source for generating a liquid fuel flow from the fuel source; a main fuel pump downstream of the draw pump; and a fuel oxygen reduction unit downstream of the draw pump and upstream of the main fuel pump.

Abstract: In one exemplary embodiment of the present disclosure, a method of operating a fuel system for an aeronautical gas turbine engine is provided. The method includes: providing a flow of fuel to a fuel nozzle of the aeronautical gas turbine engine during a wind down condition; operating a fuel oxygen reduction unit to reduce an oxygen content of the flow of fuel provided to the fuel nozzle of the aeronautical gas turbine engine during the wind down condition; and ceasing providing the flow of fuel to the fuel nozzle of the aeronautical gas turbine engine, the fuel nozzle comprising a volume of fuel after ceasing providing the flow of fuel to the fuel nozzle; wherein operating the fuel oxygen reduction unit comprises operating the fuel oxygen reduction unit to reduce an oxygen content of the volume of fuel in the fuel nozzle to less than 20 parts per million.

Abstract: A fuel oxygen reduction unit for an engine is provided. The fuel oxygen reduction unit includes an inlet fuel line; a stripping gas source; a contactor selectively in fluid communication with the stripping gas source, the inlet fuel line, or both to form a fuel/gas mixture; and a separator that receives the fuel/gas mixture, the separator configured to separate the fuel/gas mixture into an outlet stripping gas flow and an outlet fuel flow; wherein a flow of stripping gas passes through the fuel oxygen reduction unit a single time.

Abstract: An engine includes a combustion section and a fuel delivery system in fluid communication with the combustion section for providing fuel to the combustion section. The fuel delivery system includes a fuel oxygen reduction unit defining a circulation gas flowpath. The fuel oxygen reduction unit includes a gas oxygen reduction unit positioned in the circulation gas flowpath for reducing an oxygen content of a flow of stripping gas through the circulation gas flowpath and a pre-heater positioned in thermal communication with the circulation gas flowpath upstream of the gas oxygen reduction unit.