A seeder includes a housing defining a cavity, a housing gas inlet, and a seeder outlet. A sprayer is disposed within the cavity and includes a sprayer gas inlet configured to receive a gas, wherein the sprayer gas inlet is in fluid communication with the housing gas inlet. The sprayer also includes a sprayer liquid intake configured to be in fluid communication with the cavity to intake a liquid media from the cavity and a sprayer nozzle configured to be in fluid communication with the cavity above a liquid level. The sprayer is configured to combine the liquid media with the gas to spray a gas-liquid mixture through the sprayer nozzle and on to an interior spray surface of the housing.

Provided is a combustion device including: a burner that includes an ammonia injection nozzle having an injection port that faces an inner space of a furnace; and an adjustment structure that adjusts a separation distance between the injection port and the inner space.

Present disclosure relates to a injector, which comprises a first lance, provisioned with at least one first inlet port, to receive a first fluid. Further, a second lance is coaxially disposed within the first lance, and provisioned with at least one second inlet port, to receive a second fluid. The injector further includes a tube member, disposable within the second lance to receive the first fluid at one end, while sealed at another end. The tube member is provisioned with at least one recess for the first fluid in the tube member to mix with the second fluid and form the effervescent fluid. The effervescent fluid is then dispensed through at least one of a first exit port of the first lance and a second exit port of the second lance. The injector may be employed in applications such as, fuel injection, spray coating and the like.

A nozzle for a combustor is disclosed. The nozzle may include a main fuel passage (202), a number of radial fuel ports (206) in communication with the main fuel passage, a prefilmer surface (212) in communication with the radial fuel ports, and a main purge air passage (218) in communication with the radial fuel ports and the prefilmer surface.

A liquid fuel cartridge for a gas turbine fuel nozzle includes a tube having an inlet end and an outlet end with one or more fuel exit orifices; and a homogenizer located within the tube, adjacent and up-stream of the outlet end. The homogenizer is formed by a substantially-cylindrical body open at opposite ends, and a first row of circumferentially-spaced flanges projecting radially outwardly from the substantially cylindrical body, with radially-outer edges of said flanges engaged with an interior surface of the tube thereby creating a plurality of apertures for a liquid fuel and water emulsion. The homogenizer body may also be provided with a plurality of circumferentially-spaced radially-oriented orifices to promote better mixing of the fuel/water emulsion.

A method of operating a burner assembly is provided. The method generally includes transporting combustible fuel and atomization air through concentric fluid lines of the burner assembly; mixing the combustible fuel and the atomization air to atomize the combustible fuel; adjusting a flow of the combustible fuel and the atomization air to obtain atomized fuel with an air-to-fuel atomization ratio of less than 0.6; outputting the atomized fuel from a nozzle of the burner assembly; and igniting the atomized fuel to produce a flame. A burner assembly operable by the method, and a corresponding nozzle are also provided.

A nozzle is provided including a nozzle body having an upstream end and a downstream end aligned about a central axis. A discharge portion is positioned adjacent the downstream end. A bore extends inwardly from the downstream end over the length of the discharge portion. An opening is formed in the nozzle body adjacent the discharge portion. The opening is fluidly connected to the bore to provide an interior air flow passage. A main fuel channel extends from the upstream end to the discharge portion. At least one fuel flow branch extends through the discharge portion between the bore and an outer surface of the nozzle body. The fuel flow branch is fluidly coupled to the main fuel conduit to provide a fuel flow passage. The outer air cap is positioned about the outer surface of the discharge portion of the nozzle body to form an exterior air flow passage.

A method of operating a burner assembly is provided. The method includes the steps of: providing combustible fuel at the input end of the burner assembly; providing atomization air at the input end of the burner assembly; transporting the combustible fuel and the atomization air to the output end of the burner assembly through concentric fluid lines; mixing the combustible fuel and the atomization air to atomize the combustible fuel; adjusting a flow of the combustible fuel and the atomization air to obtain atomized fuel with an air-to-fuel atomization ratio of less than 0.6; outputting the atomized fuel from a nozzle at the output end of the burner assembly; and igniting the atomized fuel to produce a flame. A burner assembly operable by said method, and a corresponding nozzle are also provided.

A fuel nozzle for a combustor of a gas turbine engine includes an outer air swirler along an axis, the outer air swirler defines an outer annular air passage. An inner air swirler along the axis defines an annular fuel gas passage around the axis between the outer air swirler and the inner air swirler, the annular fuel gas passage terminates with a multiple of skewed slots.

A nozzle for a combustor is disclosed. The nozzle may include a main fuel passage (202), a number of radial fuel ports (206) in communication with the main fuel passage, a prefilmer surface (212) in communication with the radial fuel ports, and a main purge air passage (218) in communication with the radial fuel ports and the prefilmer surface.