Abstract:
A system for controlling gas turbine output for a gas turbine power plant is disclosed herein. The power plant includes a gas turbine including a combustor downstream from a compressor, a turbine downstream from the combustor and an exhaust duct downstream from the outlet of the turbine. The exhaust duct receives exhaust gas from the turbine outlet. The system further includes an exhaust damper operably connected to a downstream end of the exhaust duct. The exhaust damper increases backpressure at the turbine outlet and restricts axial exit velocity of the exhaust gas exiting the turbine outlet when the exhaust damper is partially closed. A method for controlling gas turbine output is also provided herein.
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 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 first control valve controls flow of the excess air flow along an excess air flow path to a burner module in which the excess air flow and a fuel are combusted. An exhaust of the burner module and an exhaust of the turbine component can be directed to an HRSG. 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 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 inlet of at least one of the first integral compressor and the second compressor.
Abstract:
A control system for a combustor system including a plurality of can combustors, each can combustor accommodating combustion of a plurality of combustion fluids in a combustion chamber thereof is provided. The control system may include a calculator calculating: a) a pressure drop for each respective can combustor of the plurality of can combustors between a selected combustion fluid upstream of the combustion chamber and a combustion flow within the combustion chamber of the respective can combustor, and b) a differential between the respective pressure drop for each of the plurality of can combustors and an average pressure drop across all of the plurality of can combustors. The differentials identify can-to-can variation. A controller can modify a combustion parameter of at least one can combustor to reduce the differential for the at least one can combustor. The system can work iteratively to reduce can-to-can variation.
Abstract:
A method and system to extract gas from a gas turbine having at least one gas extraction mechanism placed at the turbine section that extracts exhaust gas directly from the turbine stages through the turbine casing, providing a first exhaust gas path that extends from the turbine section through the exhaust section to the exhaust gas outlet, and a second exhaust gas path for extracted exhaust gas extending directly from the turbine stages inside the turbine casing to a duct outside of the turbine casing. The gas extraction system and method can be applied to a cogeneration system.
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:
A system and method to preemptively adjust power generation of one or more non-solar power generators based on near term solar generation capability, spinning reserve margin, and/or power grid spinning reserve forecast requirements to offset solar power generation based on geospatial regional solar conditions.
Abstract:
A combined cycle power plant includes a gas turbine having a primary flow passage, a heat recovery steam generator having a heat exchanger disposed downstream from the primary flow passage, an exhaust stack in fluid communication with the primary flow passage and disposed downstream from the heat recovery steam generator and a reversible turning gear coupled to a rotor shaft of the gas turbine. The reversible turning gear counter rotates the rotor shaft during turning gear counter rotation operation of the gas turbine and reverses flow of combustion exhaust gas from the exhaust stack through the heat exchanger and back into the primary flow passage of the gas turbine, thereby conserving thermal energy stored in the heat recovery steam generator. A method for conserving thermal energy of a combined cycle power plant during counter rotation turning gear operation of the gas turbine is also disclosed.
Abstract:
Disclosed herein are methods and systems for dispensing turbine engine anticorrosive protection. In an embodiment, a method may include selecting an anticorrosion fluid for a gas turbine engine and applying the anticorrosion fluid to the gas turbine engine.