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 combustor assembly lift system (200) comprises an exterior lift frame (220) comprising a base portion (222) and an arm portion (224), wherein the arm portion extends away from a base portion to form an interior, and, an interior combustor assembly engagement frame (240) at least partially disposed in the interior of the exterior lift frame and configured to temporarily secure to at least a portion of a combustor assembly. The interior combustor assembly engagement frame is connected to the base portion of the exterior lift frame.

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 first gas cooler provides a cooled combustion gas to the exhaust duct which mixes with the exhaust gas to provide an exhaust gas mixture to a heat exchanger downstream from the exhaust duct. The power plant further includes a fuel heater in fluid communication with the outlet of the first gas cooler.

Abstract: A power plant includes a first gas turbine and a second gas turbine. The first gas turbine includes 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 first gas cooler provides a cooled combustion gas to the exhaust duct which mixes with the exhaust gas to provide an exhaust gas mixture to a first heat exchanger downstream from the exhaust duct. At least one of a compressor and a turbine of the second gas turbine are in fluid communication with the outlet of the first gas cooler.

Abstract: A method and system for transitioning a gas turbine from burning gaseous fuel to liquid fuel and purging the liquid fuel therefrom after transfer back to the gaseous fuel are disclosed herein. The method includes pressurizing a volume of liquid fuel in an accumulator with a first volume of motive gas. A valve is opened in response to low gaseous fuel pressure in the gas turbine to permit the volume of liquid fuel to flow through a conduit to the gas turbine. A volume of flushing medium is pressurized in the accumulator with a second volume of motive gas. The valve is opened to permit at least a portion of the volume of flushing medium to flow through the conduit to flush any of the volume of liquid fuel remaining in the conduit after the gas turbine consumes the volume of liquid fuel.

Abstract: The present application provides a power generation system. The power generation system may include a gas turbine engine for creating a flow of combustion gases, a steam turbine, and a steam turbine preheating system. The steam turbine preheating system may receive an extraction of the flow of combustion gases and delivers the extraction to the steam turbine to preheat the steam turbine.

Abstract: The present application provides a multiple fuel delivery system for use with a gas turbine engine. The multiple fuel delivery system may include a first fuel tank with a first fuel therein, a second fuel tank with a second fuel therein, a mixing chamber, and a flow divider downstream of the mixing chamber. The first fuel tank may be in communication with the mixing chamber via a first fuel pump and the second fuel tank may be in communication with the mixing chamber via a second fuel pump.

Abstract: A combustor assembly lift system (200) comprises an exterior lift frame (220) comprising a base portion (222) and an arm portion (224), wherein the arm portion extends away from a base portion to form an interior, and, an interior combustor assembly engagement frame (240) at least partially disposed in the interior of the exterior lift frame and configured to temporarily secure to at least a portion of a combustor assembly. The interior combustor assembly engagement frame is connected to the base portion of the exterior lift frame.

Abstract: The present application provides a power generation system. The power generation system may include a gas turbine engine for creating a flow of combustion gases, a steam turbine, and a steam turbine preheating system. The steam turbine preheating system ay receive an extraction of the flow of combustion gases and delivers the extraction to the steam turbine to preheat the steam turbine.

Abstract: A power plant includes a first gas turbine and a second gas turbine. The first gas turbine includes 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 first gas cooler provides a cooled combustion gas to the exhaust duct which mixes with the exhaust gas to provide an exhaust gas mixture to a first heat exchanger downstream from the exhaust duct. The first gas cooler is also in fluid communication with a combustor of the second gas turbine.

Abstract: Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: commanding each GT in the set of GTs to a base load level, based upon a measured ambient condition for each GT; commanding each GT in the set of GTs to adjust a respective output to match a nominal mega-watt power output value, and subsequently measuring an actual fuel flow value for each GT; adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual fuel flow value and a nominal fuel flow value at the ambient condition; commanding each GT in the set of GTs to a part load level, the part load level representing a fraction of the base load level, and subsequently measuring an actual fuel flow value for each GT at the part load level; and calibrating the set of GTs based upon a difference between the measured actual fuel flow value at the part load level and the measured actual fuel flow value

Abstract: Methods and systems for imparting corrosion resistance to gas turbine engines are disclosed. Existing and/or supplemental piping is connected to existing compressor section air extraction piping and turbine section cooling air piping to supply water and anti-corrosion agents into areas of the gas turbine engine not ordinarily and/or directly accessible by injection of cleaning agents into the bellmouth of the turbine alone and/or repair methods. An anti-corrosion mixture is selectively supplied as an aqueous solution to the compressor and/or the turbine sections of the gas turbine engine to coat the gas turbine engine components therein with a metal passivation coating which mitigates corrosion in the gas turbine engine.

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 first gas cooler provides a cooled combustion gas to the exhaust duct which mixes with the exhaust gas to provide an exhaust gas mixture to a heat exchanger downstream from the exhaust duct. The power plant further includes a fuel heater in fluid communication with the outlet of the first gas cooler.

Abstract: A power plant includes a first gas turbine and a second gas turbine. The first gas turbine includes 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 first gas cooler provides a cooled combustion gas to the exhaust duct which mixes with the exhaust gas to provide an exhaust gas mixture to a first heat exchanger downstream from the exhaust duct. At least one of a compressor and a turbine of the second gas turbine are in fluid communication with the outlet of the first gas cooler.

Abstract: A power plant includes a first gas turbine and a second gas turbine. The first gas turbine includes 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 first gas cooler provides a cooled combustion gas to the exhaust duct which mixes with the exhaust gas to provide an exhaust gas mixture to a first heat exchanger downstream from the exhaust duct. The first gas cooler is also in fluid communication with a combustor of the second gas turbine.

Abstract: A method and system for transitioning a gas turbine from burning gaseous fuel to liquid fuel and purging the liquid fuel therefrom after transfer back to the gaseous fuel are disclosed herein. The method includes pressurizing a volume of liquid fuel in an accumulator with a first volume of motive gas. A valve is opened in response to low gaseous fuel pressure in the gas turbine to permit the volume of liquid fuel to flow through a conduit to the gas turbine. A volume of flushing medium is pressurized in the accumulator with a second volume of motive gas. The valve is opened to permit at least a portion of the volume of flushing medium to flow through the conduit to flush any of the volume of liquid fuel remaining in the conduit after the gas turbine consumes the volume of liquid fuel.

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: Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: commanding each GT in the set of GTs to a base load level, based upon a measured ambient condition for each GT; commanding each GT in the set of GTs to adjust a respective output to match a nominal mega-watt power output value, and subsequently measuring an actual fuel flow value for each GT; adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual fuel flow value and a nominal fuel flow value at the ambient condition; commanding each GT in the set of GTs to a part load level, the part load level representing a fraction of the base load level, and subsequently measuring an actual fuel flow value for each GT at the part load level; and calibrating the set of GTs based upon a difference between the measured actual fuel flow value at the part load level and the measured actual fuel flow value

Abstract: A fuel delivery system for use with a flow of heavy fuel oil for a gas turbine engine may include one or more fuel lines in communication with the gas turbine engine and a magnesium mixing system positioned upstream of the one or more fuel lines. The magnesium mixing system may include a flow of magnesium and a flow of a carrier fluid, a carrier mixing chamber to mix the flow of magnesium and the flow of the carrier fluid to form a mixed carrier flow, and a heavy fuel oil mixing chamber to mix the flow of heavy fuel oil and the mixed carrier flow.

Abstract: A system and method is provided that improves the under frequency response of gas turbines by providing a fast-response power augmentation system. The system includes a tank storing a blended mixture of motive fuel such as ethanol or methanol and demineralized water in a predetermined ratio that is provided as a diluent to be injected into the compressor bellmouth, the Compressor Discharge Chamber (CDC), and/or the combustion system via one to three dedicated circuits. To achieve the instantaneous injection of the diluent at the correct pressure and for the appropriate duration to meet the needs of the gas turbine Grid compliance mandate, an accumulator is used as the motive force to drive the augmentation fluid in the dedicated circuits. The injected diluent is microprocessor controlled to either be simultaneous into all three circuits or is sequenced based on a determination of the best turbine control and performance.