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 fuel nozzle for a combustor of an aircraft engine includes a nozzle body defining an a fuel passage, extending therethrough between a fuel inlet and a fuel outlet located at the outlet end that at least partially defines a nozzle tip, for directing a fuel flow into the combustor via the nozzle tip. A core air passage extends through the nozzle body for directing a core air flow into the combustor via the nozzle tip. At least two flow restrictors are disposed in series within the core air passage, the flow restrictors including an upstream flow restrictor and a downstream flow restrictor each having an orifice therein. The restricted air flow passage having a cross-sectional area smaller than that of the core air passage. The orifice in the upstream flow restrictor being at least partially offset from the orifice in the downstream flow restrictor.

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 improved oil preheater assembly for a waste oil burner that significantly reduces the labor time required to perform routine maintenance. This is accomplished by incorporating a removable cover to directly access the heated oil passages for cleaning thereby providing a simplified method of access to the areas most often requiring routine maintenance. Additionally this design provides an improved electrical control system which significantly reduces electrical energy consumption and the formation of oil carbonization when oil burner heat output is not required. Additionally this design incorporates a nozzle cleaning system for a low pressure siphoning type of discharge nozzle which can remove carbonization and other nozzle contamination and obstructions without the disassembly of components.

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 fuel nozzle apparatus includes: an outer body having an exterior surface and a plurality of openings in the exterior surface. An inner body is disposed inside the outer body, cooperating with the outer body to define an annular space. A main injection ring is disposed in the annular space and includes an array of fuel posts extending outward therefrom, each fuel post including a perimeter wall defining a lateral surface and a recessed floor. Each fuel post is aligned with one of the openings and separated from the opening by a perimeter gap defined between the opening and the lateral surface. A main fuel gallery extends within the main injection ring. The main injection ring includes plurality of main fuel orifices, each main fuel orifice communicating with the main fuel gallery and extending through one of the fuel posts.

A fuel nozzle apparatus includes: an outer body having an exterior surface and a plurality of openings in the exterior surface. An inner body is disposed inside the outer body, cooperating with the outer body to define an annular space. A main injection ring is disposed in the annular space and includes an array of fuel posts extending outward therefrom, each fuel post including a perimeter wall defining a lateral surface and a recessed floor. Each fuel post is aligned with one of the openings and separated from the opening by a perimeter gap defined between the opening and the lateral surface. A main fuel gallery extends within the main injection ring. The main injection ring includes plurality of main fuel orifices, each main fuel orifice communicating with the main fuel gallery and extending through one of the fuel posts.

A device for cleaning a tip of a furnace burner including a support tube of axis X intended to pass through the burner to have the burner passing through it and where the support tube includes a metal cable connected at one of its ends to a scraper and at the other end to a system for setting and maintaining the position of the scraper, in that the scraper is articulated to on the support tube between a first position aligned with the axis X in the continuation of the support tube and a second position perpendicular to the axis X, in that the scraper has a chamfered part on its profile and in that the support tube is connected to a rotation means for setting rotating the entire whole device in rotation. It can be set in place and manipulated from the rear of the burner, thereby ensuring a good level of safety for interventions such that a rotational and/or translational movement about the tip of the burner allows the concretions to be cleaned off effectively whatever their nature (shape, hardness, etc.) and their position.

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.