Abstract: Mitigating particulate intrusion to an air intake system of a gas turbine system with intrusion protective coatings tailored to locale of operation. A particulate intrusion protective coating is applied to a surface of a component of the air intake system to mitigate ingress of particulates within the air intake system and the gas turbine system. The particulate intrusion protective coating includes one or more particulate ingress influencing properties tailored to the common attributes of the particulates associated with the locale of operation of the gas turbine engine and the air intake system. The particulate ingress influencing properties affect rebounding and coalescing characteristics of the particulates at a point of impact with the applied surface having the particulate intrusion protective coating, entraining the particulates at the point of impact and inhibiting further ingress along an inlet air flow path of the air intake system into the gas turbine engine.

Abstract: A control system for turbine systems configured to utilize an intelligent model of particulate presence and accumulation within turbine systems to address engine maintenance, erosion, corrosion, and parts failure mitigation is disclosed. The control system may build an intelligent model of fluid flow based on the data value measured by at least one sensor and based on a database of known data values to provide an estimation of amount of ingress of air intake particles into the turbine system, fouling within the turbine system, erosion of at least a portion of the turbine system, and performance degradation rate of the turbine system.

Abstract: Mitigating particulate intrusion to an air intake system of a gas turbine system with intrusion protective coatings tailored to locale of operation. A particulate intrusion protective coating is applied to a surface of a component of the air intake system to mitigate ingress of particulates within the air intake system and the gas turbine system. The particulate intrusion protective coating includes one or more particulate ingress influencing properties tailored to the common attributes of the particulates associated with the locale of operation of the gas turbine engine and the air intake system. The particulate ingress influencing properties affect rebounding and coalescing characteristics of the particulates at a point of impact with the applied surface having the particulate intrusion protective coating, entraining the particulates at the point of impact and inhibiting further ingress along an inlet air flow path of the air intake system into the gas turbine engine.

Abstract: Air filtration assemblies configured to provide instant detection of particles and/or improve particle filtration are disclosed. The assemblies may include an air inlet duct in fluid communication with a compressor of a gas turbine system. The air inlet duct may include an inlet for receiving intake air including intake air particles, and an outlet positioned opposite the inlet. The assembly may also include a plurality of vane filters at the inlet, an array of fabric filters positioned in the air inlet duct, downstream of the vane filters, and a silencer assembly positioned in the air inlet duct, downstream of the fabric filters. Additionally, the assembly may include an electrostatic component positioned in the air inlet duct, downstream of the fabric filters. The electrostatic component may be configured to charge the intake air particles that pass through the vane filters and the fabric filters.

Abstract: A control system for turbine systems configured to utilize an intelligent model of particulate presence and accumulation within turbine systems to address engine maintenance, erosion, corrosion, and parts failure mitigation is disclosed. The control system may build an intelligent model of fluid flow based on the data value measured by at least one sensor and based on a database of known data values to provide an estimation of amount of ingress of air intake particles into the turbine system, fouling within the turbine system, erosion of at least a portion of the turbine system, and performance degradation rate of the turbine system.

Abstract: Air filtration assemblies configured to provide instant detection of particles and/or improve particle filtration are disclosed. The assemblies may include an air inlet duct in fluid communication with a compressor of a gas turbine system. The air inlet duct may include an inlet for receiving intake air including intake air particles, and an outlet positioned opposite the inlet. The assembly may also include a plurality of vane filters at the inlet, an array of fabric filters positioned in the air inlet duct, downstream of the vane filters, and a silencer assembly positioned in the air inlet duct, downstream of the fabric filters. Additionally, the assembly may include an electrostatic component positioned in the air inlet duct, downstream of the fabric filters. The electrostatic component may be configured to charge the intake air particles that pass through the vane filters and the fabric filters.

Abstract: Provided are water-based fuel additive compositions that, when combusted with a fuel containing vanadium in a gas turbine, inhibit vanadium hot corrosion in the gas turbine. The water-based fuel additive compositions include at least one rare earth element compound or alkaline earth element compound that retards vanadium corrosion resulting from combustion of vanadium rich fuel.

Abstract: Provided are oil-based fuel additive compositions that, when combusted with a fuel containing vanadium in a gas turbine, inhibit vanadium hot corrosion in the gas turbine. The oil-based fuel additive compositions include at least one rare earth element compound or alkaline earth element compound that retards vanadium corrosion resulting from combustion of vanadium rich fuel.

Abstract: Provided are oil-based fuel additive compositions that, when combusted with a fuel containing vanadium in a gas turbine, inhibit vanadium hot corrosion in the gas turbine. The oil-based fuel additive compositions include at least one rare earth element compound or alkaline earth element compound that retards vanadium corrosion resulting from combustion of vanadium rich fuel.

Abstract: Provided are water-based fuel additive compositions that, when combusted with a fuel containing vanadium in a gas turbine, inhibit vanadium hot corrosion in the gas turbine. The water-based fuel additive compositions include at least one rare earth element compound or alkaline earth element compound that retards vanadium corrosion resulting from combustion of vanadium rich fuel.

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 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 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: 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: 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: The present application and the resultant patent provide a wash system for a gas turbine engine. The wash system may include a water source containing a volume of water therein, and a surface filming agent source containing a volume of a surface filming agent therein. The wash system also may include a mixing chamber in fluid communication with the water source and the surface filming agent source, wherein the mixing chamber is configured to mix the water and the surface filming agent therein to produce a film-forming mixture. The wash system further may include a number of supply lines in fluid communication with the mixing chamber, wherein the supply lines are configured to direct the film-forming mixture into the gas turbine engine. The present application and the resultant patent also provide a related method of washing a gas turbine engine to remove contaminants therefrom.

Abstract: A coated article and a method for producing a coating are disclosed. Producing the coating includes providing a substrate defining a substrate surface having a substrate erosion resistance and applying a matrix and ceramic particles to the substrate surface. The matrix includes an anodic material having an anodic erosion resistance. The ceramic particles include a first ceramic having a first ceramic erosion resistance and a second ceramic having a second ceramic erosion resistance. The first ceramic erosion resistance is greater than the second ceramic erosion resistance, greater than the anodic erosion resistance, and greater than the substrate erosion resistance. The second ceramic interacts inchoately with the anodic material during the applying to form modified ceramic particles and modified anodic material formations. The modified ceramic particles are capable of forming a passive oxide film. The coated article includes the substrate and the coating on the substrate surface.

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 coating method, coated article and coating are provided. The coated article includes a low temperature component, and a graphene coating formed from a graphene derivative applied over the low temperature component. The coating method includes providing a graphene derivative, providing a low temperature component, applying the graphene derivative over the low temperature component, and forming a graphene coating. The graphene coating reduces corrosion and fouling of the low temperature component. The coating includes a graphene derivative, and modified functional groups on the graphene derivative. The modified functional groups increase adherence of the coating on application to a low temperature component.