Abstract: Spark plug assemblies and turbomachines are provided. A spark plug assembly includes a monolithic hollow cylinder extending along a longitudinal axis between a first end and a second end, the monolithic hollow cylinder including a sidewall defining an interior, a first end wall, and a second end opening. The first end wall defines a first end opening at the first end. The second end opening is defined at the second end. The spark plug assembly further includes an igniter assembly extending along the longitudinal axis into the interior through the first end opening and from the interior through the second end opening. The spark plug assembly further includes a piston surrounding the igniter, the piston disposed within the interior and extending from the interior along the longitudinal axis through the second end opening.

Abstract: An end cover for a gas turbine combustor includes a main body configured to connect to a casing that at least partially surrounds a portion of the gas turbine. A fuel circuit extends within the main body of the end cover. An orifice extends through the main body. The orifice is in fluid communication with the fuel circuit. The end cover further includes a linear actuator. The linear actuator includes a flow control member that extends the fuel circuit and at least partially through the orifice.

Abstract: A fuel nozzle assembly for use with a turbine engine is provided. The fuel nozzle assembly includes a tube that is configured to channel at least a first type of fuel through the turbine engine. A flow member includes a first end portion and a second end portion that is removably coupled to the tube such that the flow member is severally removable from the tube to enable a plurality of different types of fuel to be channeled through the turbine engine for operation of the turbine engine.

Abstract: A fuel nozzle assembly for use with a turbine engine is provided. The fuel nozzle assembly includes a tube assembly that includes a plurality of openings, wherein the tube assembly is configured to channel at least a first type of fuel through the turbine engine. A plurality of fasteners are removably coupled to the tube assembly such that each of the fasteners are severally removable from the tube assembly to enable a plurality of different types of fuel to be channeled through the turbine engine for operation of the turbine engine.

Abstract: A lubrication system and wind turbine are provided having one or more input ports in a component and one or more output ports in the component. An expandable lubrication receptacle is connected to the one or more output ports, and the expandable lubrication receptacle is configured for receiving a lubrication medium from the component.

Abstract: A system includes a fuel nozzle for a turbine engine that includes a tapered central body located at an interior base of the fuel nozzle, an air swirler, and a fuel port in the tapered central body, separate from the air swirler.

Abstract: A lubrication system and wind turbine are provided having one or more input ports in a component and one or more output ports in the component. An expandable lubrication receptacle is connected to the one or more output ports, and the expandable lubrication receptacle is configured for receiving a lubrication medium from the component.

Abstract: A combustor nozzle includes a nozzle body that defines a cavity. An orifice in the nozzle body provides fluid communication from the cavity through the nozzle body. A movable barrier proximate to the orifice has a first position in which the movable barrier at least partially obstructs the orifice. A method for supplying fuel to a combustor includes flowing fuel through an orifice in a nozzle, determining a reactivity of the fuel, and adjusting an effective cross sectional area of the orifice based on the reactivity of the fuel.

Abstract: A system, in certain embodiments, includes includes a fuel nozzle for a turbine engine that includes a tapered central body located at an interior base of the fuel nozzle, an air swirler, and a fuel port in the tapered central body, separate from the air swirler.

Abstract: A system for inserting a probe into a turbomachine. The system may include a male measurement fixture having a shaft and a female portion a housing for receiving the male measurement fixture. The male measurement fixture may include: a tip portion, an indicator, and a target zone.