Abstract: 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.

Abstract: A method for inhibiting particulate ingress in a combustion system includes acquiring particulate ingress data, determining a probable particulate ingress location on an air inlet of the combustion system in dependence upon the particulate ingress data, and deploying a filter screen at the determined probable particulate ingress location to inhibit particulate ingress at the determined probable particulate ingress location.

Abstract: A control system for turbine systems configured to provide accurate interpretations of detected particle accumulation, improve performance of turbine systems, and/or minimize costs due to downtime and maintenance are disclosed. The control system may build an intelligent model of fluid flow based on measured data provided by a sensor in a fluid flow path of the turbine system. The intelligent model consults a filter efficiency framework and determines an impact value that quantifies an operational efficiency of the turbine system and may identify a location of possible leakage, estimate a total amount of ingress of particles, identify components of the turbine system that may be operating in a diminished capacity, estimate a risk of damage to components of the turbine system, and/or recommend mitigation actions.

Abstract: A system includes an annular track that surrounds the turbomachine. The annular track includes an upper rail portion and a lower rail portion removably coupled to one another. The system further includes a drive assembly operably coupled to the annular track. The drive assembly includes a drive chain that extends along the annular track. The system further includes a plurality of carts rotatably coupled to the annular track and connected to the drive chain such that operation of the drive assembly alters a circumferential position of the plurality of carts with respect to an axial centerline of the turbomachine. The system further includes a plurality of combustion can cradle assemblies each coupled to a respective cart of the plurality of carts. Each combustion can cradle assembly of the plurality of combustion can cradle assemblies is configured to removably couple to a combustion can of the one or more combustion cans.

Abstract: A method for inhibiting particulate ingress in a combustion system includes acquiring particulate ingress data, determining a probable particulate ingress location on an air inlet of the combustion system in dependence upon the particulate ingress data, and deploying a filter screen at the determined probable particulate ingress location to inhibit particulate ingress at the determined probable particulate ingress location.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: A lift assembly includes an upper rail. A plurality of rail flanges extend from the upper rail. The lift assembly further includes a plurality of combustion can support assemblies spaced apart from one another. Each combustion can support assembly of the plurality of combustion can support assemblies includes a support flange slidably coupled to a rail flange of the plurality of rail flanges, an outer sleeve, and an inner sleeve assembly configured to removably couple to a combustion can of the turbomachine. Each combustion can support assembly of the plurality of combustion can support assemblies defines a cylindrical coordinate system having an axial direction, a radial direction, and a circumferential direction. Each combustion can support assembly of the plurality of support assemblies is configured to move along any of the axial direction, the radial direction, or the circumferential direction relative to the upper rail.

Abstract: A combined cycle power plant that includes a first gas turbine engine including a first turbine section, a second gas turbine engine including a second turbine section having an aft outlet configured to discharge an exhaust gas stream, an emissions reduction system configured to receive the exhaust gas stream discharged from the second gas turbine engine, and configured to remove oxides of nitrogen from the exhaust gas stream, and an interstage extraction system communicatively coupled with the first turbine section. The interstage extraction system is configured to selectively extract turbine extraction air from the first turbine section for providing heat to the emissions reduction system.

Abstract: A combined cycle power plant that includes a first gas turbine engine including a first turbine section, a second gas turbine engine including a second turbine section having an aft outlet configured to discharge an exhaust gas stream, an emissions reduction system configured to receive the exhaust gas stream discharged from the second gas turbine engine, and configured to remove oxides of nitrogen from the exhaust gas stream, and an interstage extraction system communicatively coupled with the first turbine section. The interstage extraction system is configured to selectively extract turbine extraction air from the first turbine section for providing heat to the emissions reduction system.

Abstract: The present application provides a gas turbine engine. The gas turbine engine may include a compressor, a compressor wash system in communication with the compressor, a condensate or boiler feed water system in communication with the compressor, and a dosing system in communication with the condensate or boiler feed water system.

Abstract: A system includes a controller communicatively coupled to a compressor. The controller is configured to sense an exhaust temperature of a gas turbine system fluidly coupled to the compressor and derive a setpoint based on the sensed exhaust temperature. The controller is also configured to actuate an inlet bleed heat valve based on the derived setpoint and an ambient temperature. The inlet bleed heat valve directs a compressor fluid from the compressor into a fluid intake system fluidly coupled to the compressor upstream of the compressor and configured to intake a fluid.

Abstract: A system includes a controller configured to control a heated flow discharged from an outlet of a mixing chamber to an inlet control system to control a temperature of an intake flow through a compressor inlet of a compressor of a gas turbine system. The controller is configured to control a turbine extraction gas (TEG) flow to the mixing chamber. The controller is configured to control at least one of a pressurized flow of the compressor to the mixing chamber and a steam flow to the mixing chamber. The TEG flow is extracted through a turbine casing. The heated flow includes the TEG flow and the at least one of the pressurized flow and the steam flow.

Abstract: A turbomachine includes a compressor configured to compress air received at an intake portion to form a compressed airflow that exits into an outlet portion. A combustor is operably connected with the compressor, and receives the compressed airflow. A turbine is operably connected with the combustor, and receives the combustion gas flow. The turbine has a plurality of wheels and a plurality of buckets. The turbine receives compressor bleed off air to cool the wheels and buckets. A cooling system is operatively connected to the turbine. The cooling system includes a plurality of heat pipes located axially upstream of at least one of the wheels. The heat pipes are operatively connected to a bearing cooler system. The heat pipes and the bearing cooler system are configured to transfer heat from the compressor bleed off air to one or more heat exchangers.

Abstract: A power plant includes an exhaust duct that receives an exhaust gas from an outlet of the turbine outlet and an ejector having a primary inlet fluidly coupled to a compressor extraction port. The ejector receives a stream of compressed air from the compressor via the compressor extraction port. The power plant further includes a static mixer having a primary inlet fluidly coupled to a turbine extraction port, a secondary inlet fluidly coupled to an outlet of the ejector and an outlet that is in fluid communication with the exhaust duct. A stream of combustion gas flows from a hot gas path of the turbine and into the inlet of the static mixer via the turbine extraction port. The static mixer receives a stream of cooled compressed air from the ejector to cool the stream of combustion gas upstream from the exhaust duct. The cooled combustion gas mixes with the exhaust gas within the exhaust duct to provide a heated exhaust gas mixture to a heat exchanger.

Abstract: A power plant includes a gas turbine including a turbine extraction port that is in fluid communication with a hot gas path of the turbine and an exhaust duct that receives exhaust gas from the turbine outlet. The power plant further includes a first gas cooler having a primary inlet fluidly coupled to the turbine extraction port, a secondary inlet fluidly coupled to a coolant supply system and an outlet in fluid communication with the exhaust duct. The power plant further includes a gas distribution manifold that is disposed downstream from the outlet of the first gas cooler and which receives a portion of the combustion gas or a portion of the cooled combustion gas and distributes the portion of the combustion gas or a portion of the cooled combustion to one or more secondary operations of the power plant.

Abstract: A system includes a controller configured to control a heated flow discharged from an outlet of an eductor to an inlet control system to control a temperature of an intake flow through a compressor inlet of a compressor of a gas turbine system. The controller is configured to control a turbine extraction gas (TEG) flow to a motive inlet of the eductor. The controller is configured to control a suction flow to a suction inlet of the eductor. The TEG flow is extracted through a turbine casing, and the heated flow includes the TEG flow and the suction flow.

Abstract: A gas turbine system includes a compressor protection subsystem; a hibernation mode subsystem; and a control subsystem that controls the compressor subsystem and the hibernation subsystem. At partial loads on the turbine system, the compressor protection subsystem maintains an air flow through a compressor at an airflow coefficient for the partial load above a minimum flow rate coefficient where aeromechanical stresses occur in the compressor. The air fuel ratio in a combustor is maintained where exhaust gas emission components from the turbine are maintained below a predetermined component emission level while operating at partial loads.