Abstract: Disclosed herein are methods and systems for treating a surface, such as a gas turbine surface, with a filming treatment. The system includes a storage tank configured to contain a filming agent, a plurality of nozzles, and supply conduit coupled to the storage tank on a first end and the plurality of nozzles on a second end, wherein the system is configured to deliver the filming agent from the storage tank and to discharge the filming agent through the plurality of nozzles 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: Disclosed herein are systems and methods for treating a surface, such as a gas turbine surface, with a filming agent using an inlet air cooling device. A filming control system includes a storage tank configured to contain a filming agent; an inlet air cooling device; and a supply conduit coupled to the storage tank on a first end and the inlet air cooling device 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 air inlet cooling device 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: Disclosed herein are systems and methods for protecting a surface from corrosive pollutants. A method includes detecting airborne corrosive pollutants proximate to a surface using at least one sensor adapted to detect a concentration of the airborne corrosive pollutants and/or one or more types of airborne corrosive pollutants, the concentration of the airborne corrosive pollutants being an instantaneous concentration value or a time-weighted-integrated concentration value; selecting a fluid to deliver to at least a portion of the surface based upon a predetermined type and/or concentration of the airborne corrosive pollutants detected by the at least one sensor; and initiating a fluid treatment to deliver the selected fluid such that the selected fluid contacts the at least a portion of the surface.

Abstract: Methods and systems for washing a surface, such as a gas turbine surface, are provided. A wash control system includes a storage tank configured to contain a cleaning agent, a plurality of nozzles, and a supply conduit coupled to the storage tank on a first end and the plurality of nozzles on a second end, wherein the wash control system is configured to deliver the cleaning agent from the storage tank and to discharge the cleaning agent through the plurality of nozzles and the cleaning agent includes an ethylene oxide-propylene oxide block copolymer, sodium dodecyl benzene sulphonate, sodium lauryl sulphate, 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 turbomachine system includes a compressor portion having at least one compressor extraction, a turbine portion operatively connected to the compressor portion, and a combustor assembly including at least one combustor fluidically connected to the compressor portion and the turbine portion. A heat recovery steam generator (HRSG) is fluidically connected to the turbine portion, and an air inlet system is fluidically connected to the compressor portion. An inlet bleed heat (IBH) system is fluidically connected to each of the compressor portion, the air inlet system and the HRSG. An inlet bleed heat (IBH) system includes a first conduit having a first valve fluidically connecting the compressor extraction and the air inlet system, and a second conduit including a second valve connecting one of the HRSG and a secondary stream source with the first conduit.

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: Various embodiments include a leak detection system for a turbine compartment. In some embodiments, the leak detection system includes: a tracer fluid system fluidly connected with the turbine compartment, the tracer fluid system configured to provide an optically detectable fluid to a fluid supply of the turbine compartment; an optical detection system operably connected to the turbine compartment, the optical detection system configured to detect the presence of the optically detectable fluid in at least one location of the turbine compartment; and a control system operably connected to the tracer fluid system and the optical detection system, the control system configured to obtain data about the presence of the optically detectable fluid in the at least one location, and provide an indicator indicating a potential leak location based upon the data about the presence of the optically detectable fluid in the at least one location.

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.

Abstract: Systems and methods for de-icing an inlet screen and dehumidifying an inlet air filter in a gas turbine engine are disclosed herein. In one embodiment, a method may include determining a current inlet screen temperature. The method also may include determining a desired inlet screen temperature. If the current inlet screen temperature is less than the desired inlet screen temperature, the method may further include determining a first amount of gas turbine compartment ventilation discharge air necessary to achieve the desired inlet screen temperature, extracting the first amount of gas turbine compartment ventilation discharge air, and conveying the first amount of gas turbine compartment ventilation discharge air to the inlet screen.

Abstract: Systems and methods for utilizing gas turbine compartment ventilation discharge air. In one embodiment, a system may include a gas turbine engine having a compressor. The system also may include a gas turbine compartment disposed about the gas turbine engine. Moreover, the system may include an inlet bleed heat (IBH) manifold in fluid communication with the compressor. The gas turbine compartment may be in fluid communication with the IBH manifold for providing the IBH manifold with ventilation discharge air from the gas turbine compartment.

Abstract: Systems and methods for preheating fuel in a gas turbine engine are provided. In one embodiment, a system may include a gas turbine engine, a fuel line in fluid communication with the gas turbine engine, a gas turbine compartment disposed about the gas turbine engine, and a first conduit in fluid communication with the gas turbine compartment. The first conduit may include ventilation discharge air from the gas turbine compartment. The system also may include a first heat exchanger in communication with the fuel line and the first conduit. The first heat exchanger may be configured to exchange heat between the fuel and the ventilation discharge air from the gas turbine compartment.

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: 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, an ambient air source with an ambient air flow, a turbine, and an eductor. The eductor blends the compressor bleed air flow and the ambient air flow into a blended air flow for use in cooling the turbine.

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 compartment with a turbine compartment air flow, a turbine, and an eductor. The eductor blends the compressor bleed air flow and the turbine compartment air flow into a blended air flow for use in cooling the turbine.

Abstract: A refurbishing method, refurbishing apparatus and refurbished article are provided. The refurbishing method includes accessing a plurality of rotatable components attached to a turbine assembly, the turbine assembly being a portion of a turbomachine, providing a predetermined volume of a buffered electrolytic solution in an electro-polishing tank, coupling the plurality of rotatable components to a power supply, immersing an immersion portion of at least one of the plurality of rotatable components in the buffered electrolytic solution, passing an electrical energy through the immersion portion of at least one of the plurality of rotatable components while the immersion portion is immersed in the buffered electrolytic solution, wherein an electrical flux to the immersion portion electro-polishes the immersion portion, separating the immersion portion from the buffered electrolytic solution, and applying a corrosion inhibitor to the plurality of rotatable components.

Abstract: A supercharging system includes a fan providing an air flow, and a prime mover that drives the fan. A duct directs a first portion of the air flow to a gas turbine system, a main bypass subsystem diverts a second portion of the air flow to a heat recovery steam generator; and a drive bypass subsystem that diverts a third portion of the air flow to the prime mover. The prime mover may be one of an aeroderivative gas turbine, a gas turbine, a reciprocating engine, a steam turbine and an induction motor and a variable frequency drive.

Abstract: A system for refurbishing at least one article attached to an assembly includes a refurbishing vessel that contains at least one wall and at least one open portion; means for providing an abrasive media to the vessel, wherein the abrasive media is caused to flow around the surfaces of the at least one article when the vessel is positioned on the at least one article; means for conformably sealing the at least one open portion against the flow of abrasive media, wherein a seal is created that conforms to the contours of the at least one article and prevents the abrasive media from escaping between the at least one article and the at least one wall; and means for removing the abrasive media from the vessel.

Abstract: A lubrication system for a heavy duty gas turbine includes a bearing lubrication assembly coupled to the bearing and an oil and vapor extraction assembly disposed in a cavity defined by a bell mouth hood in an air inlet duct. A high volume vacuum blower is coupled to the oil and vapor extraction assembly to provide a relative negative pressure. An oil and vapor separator is disposed downstream from the high volume vacuum blower. The lubrication system also includes a control subsystem that maintains a cavity pressure lower than an air inlet pressure.

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.