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 compressor, a combustor downstream from the compressor and a turbine disposed downstream from the combustor. The compressor includes a compressor extraction port. The turbine includes a turbine extraction port that is in fluid communication with a hot gas path of the turbine and which provides a flow path for a stream of combustion gas to flow out of the turbine. An exhaust duct is disposed downstream from the turbine and receives exhaust gas from the turbine. A static mixer coupled to the turbine extraction port and to the compressor extraction port cools the stream of combustion gas upstream from the exhaust duct. The cooled combustion gas flows into the exhaust duct at a higher temperature than the exhaust gas and mixes with the exhaust gas within the exhaust duct to provide a heated exhaust gas mixture to a heat exchanger downstream from the exhaust duct.

Abstract: The present application thus provides a compressor wash system for use about a bellmouth of a compressor of a gas turbine engine. The compressor wash system may include a bellmouth wash nozzle positioned about the bellmouth of the compressor and a wash door assembly positioned about a lower half of the bellmouth such that the wash door assembly may be closed when the bellmouth wash nozzle is activated.

Abstract: Disclosed herein are systems and methods for treating a surface, such as a gas turbine surface, with a filming agent using an inlet bleed heat manifold. A filming control system includes a storage tank configured to contain a filming agent; an inlet bleed heat manifold; and a supply conduit coupled to the storage tank on a first end and the inlet bleed heat manifold on a second end; wherein the filming control system is configured to deliver the filming agent from the storage tank and to discharge the filming agent through the inlet heat bleed manifold and the filming agent includes siloxane, fluorosilane, mercapto silane, amino silane, tetraethyl orthosilicate, succinic anhydride silane, or a combination including at least one of the foregoing.

Abstract: The present application provides a gas turbine engine for low turndown operations. The gas turbine engine may include a compressor with a compressor bleed air flow, a turbine, and a compressor bleed air flow manifold. The compressor bleed air manifold directs a variable portion of the compressor bleed air flow to the turbine.

Abstract: A cleaning method and a cleaning fluid are provided. The cleaning method includes accessing a plurality of turbine components attached to a turbine assembly, the turbine assembly being a portion of a turbomachine, positioning at least one cleaning vessel over at least one of the turbine components, forming a liquid seal with a sealing bladder, providing a cleaning fluid to the cleaning vessel, and draining the cleaning fluid from the cleaning vessel. The cleaning fluid includes a carrier fluid and a solvent additive for removing fouling material from the turbine component. An alternative cleaning method is also provided.

Abstract: A gas turbine engine system includes a gas turbine engine with a rotating element, at least one primary rotor shaft coupled to the rotating element, and a primary generator coupled to the at least one primary rotor shaft. The system further includes at least one auxiliary rotor shaft coupled to the at least one primary rotor shaft, such that rotation of the at least one primary rotor shaft causes rotation of the at least one auxiliary rotor shaft. The at least one auxiliary rotor shaft is oriented substantially perpendicularly to the at least one primary rotor shaft. An auxiliary generator is coupled to the at least one auxiliary rotor shaft, such that the auxiliary generator is in parallel configuration to the primary generator.

Abstract: An air disruption system for an enclosure includes an air delivery system, at least one plenum including an inlet fluidically connected to the air delivery system and at least one outlet, and a controller operatively connected to the air delivery system. The controller is configured and disposed to selectively cause one or more discrete amounts of air to pass into the at least one plenum and flow through the outlet creating a localized air disruption.

Abstract: A cleaning method and a cleaning fluid are provided. The cleaning method includes accessing a plurality of turbine components attached to a turbine assembly, the turbine assembly being a portion of a turbomachine, positioning at least one cleaning vessel over at least one of the turbine components, forming a liquid seal with a sealing bladder, providing a cleaning fluid to the cleaning vessel, and draining the cleaning fluid from the cleaning vessel. The cleaning fluid includes a carrier fluid and a solvent additive for removing fouling material from the turbine component. An alternative cleaning method is also provided.

Abstract: A system and method for supercharging a combined cycle system includes a forced draft fan providing a variable air flow. At least a first portion of the air flow is directed to a compressor and a second portion of the airflow is diverted to a heat recovery steam generator. A control system controls the airflows provided to the compressor and the heat recovery steam generator. The system allows a combined cycle system to be operated at a desired operating state, balancing cycle efficiency and component life, by controlling the flow of air from the forced draft fan to the compressor and the heat recovery steam generator.

Abstract: A system for augmenting gas turbine power output is disclosed. The system may include a gas turbine engine having a compressor, a combustor, and a turbine. The system also may include a pressurized air tank in communication with the gas turbine engine. Moreover, the system may include an external compressor in communication with the pressurized air tank. The external compressor may be configured to supply compressed air to the pressurized air tank, and the pressurized air tank may be configured to supply compressed air to the gas turbine engine.

Abstract: A method and system for measuring a flow profile in a portion of a flow path in a turbine engine is provided. The system includes a mass flow sensor assembly having a plurality of hot wire mass flow sensors, the mass flow sensor assembly disposed in the portion of the flow path at a location where the flow profile is to be measured. The system also includes a controller that converts signals from the temperature sensor, the pressure sensor and the plurality of hot wire mass flow sensors to flow profile measurements.

Abstract: Disclosed are methods and systems to determine a power plant machine reliability forecast. In an embodiment, a method may comprise obtaining an environmental factor of a power plant machine based on geospatial data of a first area and location data of a second area, obtaining an operating factor of the power plant machine, and determining a reliability forecast based on the obtained environmental factor and the obtained operating factor.

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 combustion gas flow from the combustor. The turbine has a plurality of wheels and a plurality of buckets, and the turbine receives compressor bleed off air to cool at least one of the wheels. A cooling system is operatively connected to the turbine, and includes a plurality of heat pipes attached to or embedded within at least one of the wheels. The compressor bleed off air is configured to impinge onto at least one of the wheels or the heat pipes. The heat pipes and the compressor bleed off air are configured to cool the wheels.

Abstract: A turbomachine includes a compressor, combustor and a turbine. An intercooler is operatively connected to the compressor. The intercooler includes a first plurality of heat pipes that extend into the inter-stage gap of the compressor, and the heat pipes are operatively connected to a first manifold. The heat pipes and the manifold are configured to transfer heat from the compressed airflow to one or more heat exchangers. A first cooling system is operatively connected to the turbine. The first cooling system includes a second plurality of heat pipes attached to or embedded within at least one of the plurality of wheels. The compressor bleed off air is configured to impinge onto at least one of the plurality of wheels or the second plurality of heat pipes. The second plurality of heat pipes and the compressor bleed off air are configured to cool at least one of the plurality of wheels.

Abstract: A turbomachine includes a compressor having an inter-stage gap between adjacent rows of rotor blades and stator vanes. A combustor is connected to the compressor, and a turbine is connected to the combustor. An intercooler is operatively connected to the compressor, and includes a first plurality of heat pipes that extend into the inter-stage gap. The first plurality of heat pipes are operatively connected to a first manifold, and the heat pipes and the first manifold are configured to transfer heat from the compressed airflow from the compressor to heat exchangers. A cooling system is operatively connected to the turbine, and includes a second plurality of heat pipes located in the turbine nozzles. The second plurality of heat pipes are operatively connected to a second manifold, and the heat pipes and the second manifold are configured to transfer heat from the turbine nozzles to the heat exchangers.

Abstract: A power generation system may include a gas turbine system including a turbine component, an integral compressor and a combustor to which air from the integral compressor and fuel are supplied. The combustor is arranged to supply hot combustion gases to the turbine component, and the integral compressor has a flow capacity greater than an intake capacity of the combustor and/or the turbine component, creating an excess air flow. A turbo-expander powers a generator. A first control valve controls flow of the excess air flow along an excess air flow path to the turbo-expander. An eductor may be positioned in the excess air flow path for using the excess air flow as a motive force to augment the excess air flow with additional air.

Abstract: A power generation system includes: a first gas turbine system including a first turbine component, a first integral compressor and a first combustor to which air from the first integral compressor and fuel are supplied, the first combustor arranged to supply hot combustion gases to the first turbine component, and the first integral compressor having a flow capacity greater than an intake capacity of the first combustor and/or the first gas turbine component, creating an excess air flow. A second gas turbine system may include similar components to the first except but without excess capacity in its compressor. A control valve system controls flow of the excess air flow from the first gas turbine system to the second gas turbine system. A heat exchanger may be coupled to the excess air flow path for exchanging heat with the excess air flow.

Abstract: A power generation system may include: a first gas turbine system including a first turbine component, a first integral compressor and a first combustor to which air from the first integral compressor and fuel are supplied. The first integral compressor has a flow capacity greater than an intake capacity of the first combustor and/or the first turbine component, creating an excess air flow. A second gas turbine system may include similar components to the first except but without excess capacity in its compressor. A turbo-expander may be operatively coupled to the second gas turbine system. Control valves may control flow of the excess air flow from the first gas turbine system to at least one of the second gas turbine system and the turbo-expander, and flow of a discharge of the turbo-expander to an exhaust of at least one of the first turbine component and the second turbine component.