System and method for mitigating particulate intrusion to an air intake system of a gas turbine system with intrusion protective coatings tailored to locale of operation

A method, comprising:

• determining a locale of operation of an air intake system of a gas turbine system having a gas turbine engine;
• ascertaining common attributes of particulates associated with the determined locale of operation that are expected to be ingested by the air intake system and the gas turbine system while operating in the determined locale of operation;
• customizing a particulate intrusion protective coating for application to a surface of a component of an inlet filter house of the air intake system with properties that mitigate ingress of the particulates within the air intake system and the gas turbine system for operation in the determined locale, wherein the customizing of the particulate intrusion protective coating includes altering a chemical composition of the particulate intrusion protective coating to have one or more particulate ingress influencing properties tailored to the ascertained common attributes of the particulates associated with the determined locale of operation, wherein the particulate ingress influencing properties affect rebounding, coalescing, and hydrophilic characteristics of the particulates at a point of impact with the surface of the component of the inlet filter house having the particulate intrusion protective coating, wherein the customizing of the particulate intrusion protective coating comprising adjusting the particulate ingress influencing properties of the particulate intrusion protective coating to achieve one or more of a low rebounding effect and a high rebounding effect of the particulates at the point of impact with the component having the particulate intrusion protective coating, wherein the customized particulate intrusion protective coating is a multi-layered particulate intrusion protective coating comprising a top layer having 10-75 wt. % Polyurethane+5-40 wt. % Epoxy composition, and a bottom layer deposited on a substrate having 10-75 wt. % Epoxy+5-40 wt. % PU;
• and
• applying the customized particulate intrusion protective coating to the surface of one or more components of the inlet filter house, wherein the customized particulate intrusion protective coating applied to the surface of the one or more components of the inlet filter house entrains the particulates at the point of impact, and inhibits further ingress along the inlet air flow path of the air intake system from the inlet filter house into the gas turbine engine.

A gas turbine system, comprising:

• a gas turbine engine;
• an air intake system operatively coupled to the gas turbine engine to direct a stream of inlet air to the gas turbine engine, the air intake system comprising an inlet filter house having a weather hood with a plurality of inlet vane separators and a plurality of moisture separators to permit passage of the stream of inlet air while preventing passage of weather elements, a filter module to filter the stream of inlet air passing through the weather hood, a cooling module to adjust the temperature of the filtered stream of inlet air, and a plurality of drift eliminators to protect against water carry-over from the cooling module;
• and
• a particulate intrusion protective coating applied to a surface of one or more of the plurality of inlet vane separators, the plurality of moisture separators, and the plurality of drift eliminators, wherein the particulate intrusion protective coating includes one or more particulate ingress influencing properties tailored to common attributes of particulates associated with a locale of operation of the gas turbine engine and the air intake system, wherein the particulate ingress influencing properties affect rebounding, coalescing, and hydrophilic 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, wherein the particulate intrusion protective coating is a multi-layer coating comprising one or more polyurethane layer and one or more epoxy layer, wherein the one or more polyurethane layer and the one or more epoxy layer are tailored to attain a desired rebounding and coalescing effect on the particulates at the point of impact with the component, and wherein the multi-layered particulate intrusion protective coating comprises a top layer having 10-75 wt. % Polyurethane+5-40 wt. % Epoxy composition, and a bottom layer deposited on a substrate having 10-75 wt. % Epoxy+5-40 wt. % Polyurethane.