Abstract: A component configured to be in contact with a hydrocarbon fluid and a method of preparing a contact surface of the component. The component may include a wall having the contact surface configured to be in contact with the hydrocarbon fluid. The contact surface is formed from a metal comprising a metal M, where M is selected from the group consisting of nickel (Ni), palladium (Pd), and platinum (Pt). A metal-ligand complex comprising phosphorus (P) is on the contact surface. The method of preparing a contact surface of the component may include treating the contact surface with a metal-ligand complex precursor comprising a phosphorus (P) ligand.

Abstract: A hydrocarbon fluid containment article having a wall with a surface that is wetted by hydrocarbon fluid. The surface includes an anti-coking coating. The anti-coking coating includes a copper salt, a silver salt, or a combination thereof. A gas turbine engine component including a wall having a first surface and an anti-coking coating on the first surface of the wall that is wetted by hydrocarbon fluid. The anti-coking coating including a copper salt, a silver salt, or a combination thereof that prevents the formation of gum or coke on a surface thereon. Methods for reducing the deposition of thermal decomposition products on a wall of an article are also provided.

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: A hydrocarbon fluid containment article having a wall with a surface that is wetted by hydrocarbon fluid. The surface includes an anti-coking coating. The anti-coking coating includes a copper salt, a silver salt, or a combination thereof. A gas turbine engine component including a wall having a first surface and an anti-coking coating on the first surface of the wall that is wetted by hydrocarbon fluid. The anti-coking coating including a copper salt, a silver salt, or a combination thereof that prevents the formation of gum or coke on a surface thereon. Methods for reducing the deposition of thermal decomposition products on a wall of an article are also provided.

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: A component configured to be in contact with a hydrocarbon fluid and a method of preparing a contact surface of the component. The component may include a wall having the contact surface configured to be in contact with the hydrocarbon fluid. The contact surface is formed from a metal comprising a metal M, where M is selected from the group consisting of nickel (Ni), palladium (Pd), and platinum (Pt). A metal-ligand complex comprising phosphorus (P) is on the contact surface. The method of preparing a contact surface of the component may include treating the contact surface with a metal-ligand complex precursor comprising a phosphorus (P) ligand.

Abstract: A component configured to be in contact with a hydrocarbon fluid and a method of preparing a contact surface of the component. The component may include a wall having the contact surface configured to be in contact with the hydrocarbon fluid. The contact surface is formed from a metal comprising a metal M, where M is selected from the group consisting of nickel (Ni), palladium (Pd), and platinum (Pt). A metal-ligand complex comprising phosphorus (P) is on the contact surface. The method of preparing a contact surface of the component may include treating the contact surface with a metal-ligand complex precursor comprising a phosphorus (P) ligand.

Abstract: A component configured to be in contact with a hydrocarbon fluid and a method of preparing a contact surface of the component. The component may include a wall having the contact surface configured to be in contact with the hydrocarbon fluid. The contact surface is formed from a metal comprising a metal M, where M is selected from the group consisting of nickel (Ni), palladium (Pd), and platinum (Pt). A metal-ligand complex comprising phosphorus (P) is on the contact surface. The method of preparing a contact surface of the component may include treating the contact surface with a metal-ligand complex precursor comprising a phosphorus (P) ligand.

Abstract: A hydrocarbon fluid containment article having a wall with a surface that is wetted by hydrocarbon fluid. The surface includes an anti-coking coating. The anti-coking coating includes a copper salt, a silver salt, or a combination thereof. A gas turbine engine component including a wall having a first surface and an anti-coking coating on the first surface of the wall that is wetted by hydrocarbon fluid. The anti-coking coating including a copper salt, a silver salt, or a combination thereof that prevents the formation of gum or coke on a surface thereon. Methods for reducing the deposition of thermal decomposition products on a wall of an article are also provided.

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: 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 gas turbine engine includes a combustion section, the combustion section including a plurality of fuel nozzles. A fuel delivery system for the gas turbine engine includes a feed tube and a fuel manifold fluidly connected to the feed tube for receiving fuel from the feed tube. The fuel delivery system also includes a pigtail fuel line fluidly connected to the fuel manifold and configured to fluidly connect to a fuel nozzle of the plurality of fuel nozzles when the fuel delivery system is installed in the gas turbine engine. In order to reduce an amount of hydraulic instability of a fuel flow through the fuel delivery system, at least one of the fuel manifold or the pigtail fuel line includes a means for damping a hydraulic instability within the fuel delivery system.

Abstract: A fuel nozzle for a gas turbine engine includes an outer body extending generally along a centerline axis and defining a plurality of openings in an exterior surface. The fuel nozzle additionally includes a main injection ring disposed at least partially inside the outer body, the main injection ring including a fuel post extending into or through one of the plurality of openings of the outer body. The fuel post defines a spray well and a main fuel orifice, the spray well defining a bottom surface, a side wall, and a taper in the bottom surface extending from the main fuel orifice towards the side wall.

Abstract: The present disclosure is directed to a fuel nozzle assembly for a gas turbine engine. The fuel nozzle assembly includes a centerbody extended along a nozzle centerline axis and generally concentric thereto and an outer sleeve surrounding the centerbody and extended along the nozzle centerline axis and generally concentric thereto. The centerbody defines an outer wall extended at least partially along the nozzle centerline axis in which the centerbody defines a first fuel passage therewithin and one or more first fuel exit openings through the outer wall. Each first fuel exit opening is discrete from another along the outer wall. The outer sleeve and centerbody together define a first air passage therebetween. The first fuel passage and the first fuel exit opening are in fluid communication with the first air passage.

Abstract: A fuel nozzle for a gas turbine engine includes an outer body defining a plurality of openings in an exterior surface. The fuel nozzle also includes a main injection ring disposed at least partially inside the outer body. The main injection ring includes a plurality of fuel posts extending into or through the plurality of openings of the outer body. The plurality of fuel posts include an LP fuel post defining a main fuel orifice, a top surface, and a scarf, the scarf of the LP fuel post extending in the top surface in a first direction relative to the centerline axis away from the main fuel orifice. The plurality of fuel posts also include an HP fuel post defining a main fuel orifice, a top surface, and a scarf, the scarf of the HP fuel post extending in the top surface f in a second direction relative to the centerline axis away from the main fuel orifice, the second direction being at least ninety degrees different than the first direction.

Abstract: The present disclosure is directed to a fuel nozzle assembly for a gas turbine engine. The fuel nozzle assembly includes a centerbody extended along a nozzle centerline axis and generally concentric thereto and an outer sleeve surrounding the centerbody and extended along the nozzle centerline axis and generally concentric thereto. The centerbody defines an outer wall extended at least partially along the nozzle centerline axis in which the centerbody defines a first fuel passage therewithin and one or more first fuel exit openings through the outer wall. Each first fuel exit opening is discrete from another along the outer wall. The outer sleeve and centerbody together define a first air passage therebetween. The first fuel passage and the first fuel exit opening are in fluid communication with the first air passage.

Abstract: A fuel nozzle is provided for a gas turbine engine, and can include a pilot fuel injector having an axially-elongated, inner pilot centerbody wall and an outer pilot centerbody wall, with the axially-elongated, inner pilot centerbody wall extending from an upstream end to an annular fuel passage defining the downstream end of the pilot fuel injector. The fuel passage intersects with the inner pilot centerbody wall at a pilot fuel metering orifice. The fuel nozzle also includes a pilot fuel film surface downstream from the annular fuel passage and an annular splitter surrounding the pilot fuel injector. The annular splitter comprises, in axial sequence: an upstream section, a splitter throat having a diameter that is larger than a downstream diameter defined by the pilot fuel film surface, and a downstream diverging surface having an average diverging angle of about 24° to about 40° in relation to a centerline axis.

Abstract: A fuel nozzle for a gas turbine engine includes an outer body defining a plurality of openings in an exterior surface. The fuel nozzle also includes a main injection ring disposed at least partially inside the outer body. The main injection ring includes a plurality of fuel posts extending into or through the plurality of openings of the outer body. The plurality of fuel posts include an LP fuel post defining a main fuel orifice, a top surface, and a scarf, the scarf of the LP fuel post extending in the top surface in a first direction relative to the centerline axis away from the main fuel orifice. The plurality of fuel posts also include an HP fuel post defining a main fuel orifice, a top surface, and a scarf, the scarf of the HP fuel post extending in the top surface fin a second direction relative to the centerline axis away from the main fuel orifice, the second direction being at least ninety degrees different than the first direction.

Abstract: A fuel nozzle for a gas turbine engine includes an outer body extending generally along a centerline axis and defining a plurality of openings in an exterior surface. The fuel nozzle additionally includes a main injection ring disposed at least partially inside the outer body, the main injection ring including a fuel post extending into or through one of the plurality of openings of the outer body. The fuel post defines a spray well and a main fuel orifice, the spray well defining a bottom surface, a side wall, and a taper in the bottom surface extending from the main fuel orifice towards the side wall.