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 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 amine 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 and 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 amine 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 and at least one of the plurality of late lean fuel injectors.

Embodiments of the present disclosure generally relate to methods for cleaning aerospace components having oxidation, corrosion, contaminants, and/or other degradations. In one or more embodiments, a cleaning method includes positioning the aerospace component into a processing region of a processing chamber, introducing hydrogen gas into the processing region, maintaining the processing region at a pressure of about 100 mTorr to about 5,000 mTorr, and heating the aerospace component at a temperature of about 500° C. to about 1,200° C. for about 0.5 hours to about 24 hours to produce a cleaned surface on the aerospace component. In other embodiments, a cleaning method includes exposing the aerospace component to ozone while maintaining the aerospace component at a temperature of about 15° C. to about 500° C. for 0.25 hours to about 24 hours to produce a cleaned surface on the aerospace component.

An oxy-acetylene cutting torch tip cleaner includes an elongated body portion with at least one actuator and at least one associated housing bore for storing a cleaning pin. Each cleaning pin is coupled to an actuator movable from a first position with the cleaning pin contained in the housing bore to a second position with the cleaning pin extending from the housing bore, for abrading and cleaning the cutting torch tip. Each actuator, coupled to its cleaning pin with a slider, is biased to the first position and a lock engages each actuator in the second position such that when the lock is disengaged from the actuator at the second position with the cleaning tip extended from the body, the actuator automatically returns to the first position thereby retracting the cleaning pin back into the housing bore.

An oxy-acetylene cutting torch tip cleaner includes an elongated body portion with at least one actuator and at least one associated housing bore for storing a cleaning pin. Each cleaning pin is coupled to an actuator movable from a first position with the cleaning pin contained in the housing bore to a second position with the cleaning pin extending from the housing bore, for abrading and cleaning the cutting torch tip. Each actuator, coupled to its cleaning pin with a slider, is biased to the first position and a lock engages each actuator in the second position such that when the lock is disengaged from the actuator at the second position with the cleaning tip extended from the body, the actuator automatically returns to the first position thereby retracting the cleaning pin back into the housing bore.

A burner assembly system is disposed in a rear side, i.e. back side, of a deep fryer. The burner assembly system includes an aperture disposed in a side of a bottom portion at the rear of a fryer cabinet of the controlled deep fryer. A burner at the rear of the fryer cabinet is coupled to the aperture and is adapted to receive fuel that enters through the aperture. An ignition assembly is disposed within the burner and ignites the received fuel. A flue is disposed at the rear of and within the fryer cabinet and receives combustion gases and heat from the burner created by the ignition of fuel. A heat exchanger is disposed within the flue at the rear of the fryer cabinet and is heated by heat conveyed through the flue from the ignition of fuel in the burner.

A head assembly for a radiant burner, an inlet assembly and a method are disclosed. The head assembly is for a radiant burner. The head assembly may include a housing defining a plurality of identical housing apertures extending therethrough, an insulator received by the housing and defining a corresponding plurality of identical, complimentarily-located insulator apertures extending therethrough, and at least one inlet assembly configured to be received by one of the identical housing apertures. Each inlet assembly may include a housing portion configured to be received by the one of the identical housing apertures, and an insulator portion configured to fill the complimentarily-located insulator aperture. In this way, a head assembly is provided which has a number of apertures, any of which may receive an inlet assembly. Given that each inlet assembly is configured to be received by any of the apertures, this provides flexibility for the insertion and removal of the assemblies, without needing to completely disassemble the head assembly from the radiant burner. Also, by forming the inlet assembly with a housing portion and insulation portion, the assembly can be located within the head assembly and the insulating portion prevents heat damage.

A head assembly for a radiant burner, an inlet assembly and a method are disclosed. The head assembly is for a radiant burner. The head assembly may include a housing defining a plurality of identical housing apertures extending therethrough, an insulator received by the housing and defining a corresponding plurality of identical, complimentarily-located insulator apertures extending therethrough, and at least one inlet assembly configured to be received by one of the identical housing apertures. Each inlet assembly may include a housing portion configured to be received by the one of the identical housing apertures, and an insulator portion configured to fill the complimentarily-located insulator aperture. In this way, a head assembly is provided which has a number of apertures, any of which may receive an inlet assembly. Given that each inlet assembly is configured to be received by any of the apertures, this provides flexibility for the insertion and removal of the assemblies, without needing to completely disassemble the head assembly from the radiant burner. Also, by forming the inlet assembly with a housing portion and insulation portion, the assembly can be located within the head assembly and the insulating portion prevents heat damage.