A burner for a metal-melting furnace can releasably receive a tapered plug in sealing engagement with an access passage aligned with an air passage. The burner may be configured to extend through a wall of the metal-melting furnace so that the air passage is through a front face within the furnace and so that the access passage is through a rear face outside of the furnace. The access passage may be aligned with the air passage to permit a rigid structure to be passed through the burner from outside the furnace to dislodge build-up of solidified metal from the air passage. The tapered plug may be moveable between a sealing configuration of being received in a seat to seal the access passage during burner operation and a cleaning configuration of being removed from the seat to expose the access passage for insertion of the rigid structure.

A burner for a metal-melting furnace can releasably receive a tapered plug in sealing engagement with an access passage aligned with an air passage. The burner may be configured to extend through a wall of the metal-melting furnace so that the air passage is through a front face within the furnace and so that the access passage is through a rear face outside of the furnace. The access passage may be aligned with the air passage to permit a rigid structure to be passed through the burner from outside the furnace to dislodge build-up of solidified metal from the air passage. The tapered plug may be moveable between a sealing configuration of being received in a seat to seal the access passage during burner operation and a cleaning configuration of being removed from the seat to expose the access passage for insertion of the rigid structure.

A method of cleaning a gas inlet nozzle of an abatement burner combustion chamber. The abatement burner intermittently receives gas for combustion from a feed process. The nozzle comprises a cleaning mechanism including a movable cleaning member for physically removing unwanted deposits from the nozzle. The cleaning member is movable from a retracted first position wherein the cleaning member is outside a path of a flame associated with the nozzle, to a second cleaning position wherein the cleaning member is in a path of the flame associated with the nozzle. The method comprises the steps of: a. identifying when the nozzle is out of use; b. moving the cleaning member from the first position to the second position while the nozzle is out of use; and c. returning the cleaning member to the first position before nozzle is in use.

A method of cleaning a gas inlet nozzle of an abatement burner combustion chamber. The abatement burner intermittently receives gas for combustion from a feed process. The nozzle comprises a cleaning mechanism including a movable cleaning member for physically removing unwanted deposits from the nozzle. The cleaning member is movable from a retracted first position wherein the cleaning member is outside a path of a flame associated with the nozzle, to a second cleaning position wherein the cleaning member is in a path of the flame associated with the nozzle. The method comprises the steps of: a. identifying when the nozzle is out of use; b. moving the cleaning member from the first position to the second position while the nozzle is out of use; and c. returning the cleaning member to the first position before nozzle is in use.

A gas turbine engine system includes a compressor, gas turbine, and combustor including a plurality of late lean fuel injectors supplied with secondary fuel to its interior. The gas turbine engine system includes a wash system in communication with the late lean fuel injectors. The wash system includes a water source; water pump; anti-corrosion agent fluid source with an anti-corrosion agent including a polyamine corrosion inhibitor; anti-corrosion agent supply piping in fluid communication with the anti-corrosion agent fluid source; mixing chamber receiving water and anti-corrosion agent to produce an anti-corrosion mixture in fluid communication with the mixing chamber and the plurality of late lean fuel injectors. Fluid from the mixing chamber including the water, the anti-corrosion agent fluid source, or a mixture thereof is injected, while the gas turbine engine is off-line, into the combustor at at least one of the plurality of late lean fuel injectors.

A gas turbine engine system includes a compressor, gas turbine, and combustor including a plurality of late lean fuel injectors supplied with secondary fuel to its interior. The gas turbine engine system includes a wash system in communication with the late lean fuel injectors. The wash system includes a water source; water pump; anti-corrosion agent fluid source with an anti-corrosion agent including a polyamine corrosion inhibitor; anti-corrosion agent supply piping in fluid communication with the anti-corrosion agent fluid source; mixing chamber receiving water and anti-corrosion agent to produce an anti-corrosion mixture in fluid communication with the mixing chamber and the plurality of late lean fuel injectors. Fluid from the mixing chamber including the water, the anti-corrosion agent fluid source, or a mixture thereof is injected, while the gas turbine engine is off-line, into the combustor at at least one of the plurality of late lean fuel injectors.

A gas turbine engine system includes a gas turbine engine including a compressor, combustor including a plurality of late lean fuel injectors supplied with secondary fuel; gas turbine, and wash system configured to be attached and in fluid communication with the late lean fuel injectors. The wash system includes a water source including water; first fluid source including a first fluid providing vanadium ash and vanadium deposit mitigation and removal from internal gas turbine components; a mixing chamber in communication with the water source and first fluid source; a water pump to pump the water to the mixing chamber; a first fluid pump the first fluid to the mixing chamber; a fluid line in fluid communication with the mixing chamber and late lean fuel injectors so fluid from the mixing chamber is injected into the combustor at the late lean fuel injectors while the gas turbine engine is on-line.

A gas turbine engine system includes a gas turbine engine including a compressor, combustor including a plurality of late lean fuel injectors supplied with secondary fuel; gas turbine, and wash system configured to be attached and in fluid communication with the late lean fuel injectors. The wash system includes a water source including water; first fluid source including a first fluid providing vanadium ash and vanadium deposit mitigation and removal from internal gas turbine components; a mixing chamber in communication with the water source and first fluid source; a water pump to pump the water to the mixing chamber; a first fluid pump the first fluid to the mixing chamber; a fluid line in fluid communication with the mixing chamber and late lean fuel injectors so fluid from the mixing chamber is injected into the combustor at the late lean fuel injectors while the gas turbine engine is on-line.

A system comprises a gas turbine engine including a compressor, combustor, gas turbine, the combustor including a plurality of late lean fuel injectors; and wash system configured to be attached to and in fluid communication with the a plurality of late lean fuel injectors of the combustor. The wash system includes a water source supplying water; a first fluid source supplying a first fluid; a mixing chamber in communication with the water source and first fluid source; a water pump to pump water to the mixing chamber; a first fluid pump to pump the first fluid to the mixing chamber; a fluid line in fluid communication with the mixing chamber and at least one of the plurality of late lean fuel injectors so fluid from the mixing chamber is injected into the combustor at late lean fuel injectors. The wash system is operated with the gas turbine engine off-line.

A system comprises a gas turbine engine including a compressor, combustor, gas turbine, the combustor including a plurality of late lean fuel injectors; and wash system configured to be attached to and in fluid communication with the a plurality of late lean fuel injectors of the combustor. The wash system includes a water source supplying water; a first fluid source supplying a first fluid; a mixing chamber in communication with the water source and first fluid source; a water pump to pump water to the mixing chamber; a first fluid pump to pump the first fluid to the mixing chamber; a fluid line in fluid communication with the mixing chamber and at least one of the plurality of late lean fuel injectors so fluid from the mixing chamber is injected into the combustor at late lean fuel injectors. The wash system is operated with the gas turbine engine off-line.