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.

A combustion chamber for a gas turbine is provided. The combustion chamber has a pilot burner device, a fuel injector, an ignitor unit and an air blast injector. The pilot burner device has a pilot body with a pilot surface facing an inner volume of the combustion chamber. The fuel injector has a fuel outlet for injecting a fuel into the inner volume, wherein the fuel outlet is arranged at the pilot surface. The ignitor unit is arranged at the pilot surface such that fuel which passes the ignitor unit is ignitable. The air blast injector is adapted for injecting an air blast into the inner volume, wherein the air blast injector includes an air blast outlet arranged at the pilot surface such that the air blast is injectable in the direction to the fuel outlet and the ignitor unit for directing the fuel to the ignitor unit.

A combustion chamber for a gas turbine is provided. The combustion chamber has a pilot burner device, a fuel injector and an ignitor unit. The pilot burner device has a pilot body with a pilot surface which is facing an inner volume of the combustion chamber. The fuel injector has a fuel outlet for injecting a fuel into the inner volume. The ignitor unit is adapted for igniting the fuel inside the inner volume, wherein the ignitor unit is arranged at the pilot surface such that fuel which passes the ignitor unit is ignitable. The pilot body includes a recess, wherein the fuel outlet is arranged within the recess.

A swirler includes an inner body defining a swirl axis. A plurality of swirl vanes extend outward from the inner body. The swirl vanes define respective swirl slots therebetween for imparting swirl on a fluid passing through the swirl slots. A method of making swirlers includes additively manufacturing a stack of swirlers.

The present disclosure is generally directed to a burner and boiler/furnace for pressurized oxy-combustion boilers and furnaces. The disclosure includes a design of a burner and boiler for a staged, pressurized oxy-combustion (SPOC) technology process and designs that affect wall heat flux. The disclosure further includes the introduction of wall rings to increase, for example, advection.

A swirler includes an inner body defining a swirl axis. A plurality of swirl vanes extend outward from the inner body. The swirl vanes define respective swirl slots therebetween for imparting swirl on a fluid passing through the swirl slots. A method of making swirlers includes additively manufacturing a stack of swirlers.

A multi-functional fuel nozzle (10) for a combustion turbine engine is provided. An annular fuel-injecting lance (12) may include a first fluid circuit (14) and a second fluid circuit (16). One of the first and second fluid circuits during a liquid fuel operating mode of the combustion turbine engine may convey a liquid fuel. The other of the first and second fluid circuits may convey a selectable non-fuel fluid. An atomizer (30) is disposed at the downstream end of the lance. The atomizer may have a first ejection orifice (32) responsive to the first fluid circuit to form a first atomized ejection cone (34), and a second ejection orifice (36) responsive to the second fluid circuit to form a second atomized ejection cone (38). The first and second ejection cones (34, 38) formed with the atomizer may be concentric cones that intersect with one another over a predefined angular range.

A multi-functional fuel nozzle (10) for a combustion turbine engine is provided. An annular fuel-injecting lance (12) may include a first fluid circuit (14) and a second fluid circuit (16). One of the first and second fluid circuits during a liquid fuel operating mode of the combustion turbine engine may convey a liquid fuel. The other of the first and second fluid circuits may convey a selectable non-fuel fluid. An atomizer (30) is disposed at the downstream end of the lance. The atomizer may have a first ejection orifice (32) responsive to the first fluid circuit to form a first atomized ejection cone (34), and a second ejection orifice (36) responsive to the second fluid circuit to form a second atomized ejection cone (38). The first and second ejection cones (34, 38) formed with the atomizer may be concentric cones that intersect with one another over a predefined angular range.

Apparatus includes a first and second conduits configured to form an annulus between them. An adjustable structure includes a body having an upper surface, a lower surface, and a circumferential surface abutting a portion of the internal surface of the second conduit. The structure is adjustable axially in relation to and removably attached to the first conduit via a hub. The hub defines a central passage for fuel or oxidant. The body has one or more non-central through passages configured such that flow of an oxidant or fuel therethrough causes the fuel or oxidant to intersect flow of fuel or oxidant exiting from the central passage in a region above the upper surface of the body.

Apparatus includes a first and second conduits configured to form an annulus between them. An adjustable structure includes a body having an upper surface, a lower surface, and a circumferential surface abutting a portion of the internal surface of the second conduit. The structure is adjustable axially in relation to and removably attached to the first conduit via a hub. The hub defines a central passage for fuel or oxidant. The body has one or more non-central through passages configured such that flow of an oxidant or fuel therethrough causes the fuel or oxidant to intersect flow of fuel or oxidant exiting from the central passage in a region above the upper surface of the body.