A gas turbine system , comprising: a gas turbine engine ; an air intake system to intake air for supply to the gas turbine engine , the air intake system comprising an air filter inlet house to filter the intake air, wherein the air filter inlet house includes at least one filter stage having an array of pulse filters , with each of the pulse filters being hydrophobic, a combustion inlet air path in fluid communication with the air intake system and the gas turbine engine , the combustion inlet air path receiving the filtered air from the air filter inlet house and supplying the filtered air as combustion inlet air to an inlet of the gas turbine engine ; and a foreign object damage (FOD) screen in the combustion inlet air path between the air filter inlet house and the inlet of the gas turbine engine to prevent debris from entering the inlet of the gas turbine engine , characterised in that the FOD screen includes one or more mesh screens and an air sock placed over the one or more mesh screens , the one or more mesh screens enclosed in a frame structure having horizontally and vertically extending rails defining individual segments of sub-frame structures formed by intersections of the horizontally extending rails with the vertically extending rails, each individual segment of sub-frame structures enclosing portions of the one or more mesh screens , wherein a surface of each of the one or more mesh screens in the individual segments of sub-frame structures and the air sock placed over the one or more screens comprises an anti-icing coating to prevent ice formation thereon, the anti-icing coating applied to each of the one or more mesh screens in the individual segments of sub-frame structures and the air sock in locations where there is direct particle impact with particles flowing through the combustion inlet air path and locations without direct particle impact with the particles flowing through the combustion inlet air path. a gas turbine engine ; an air intake system to intake air for supply to the gas turbine engine , the air intake system comprising an air filter inlet house to filter the intake air, wherein the air filter inlet house includes at least one filter stage having an array of pulse filters , with each of the pulse filters being hydrophobic, a combustion inlet air path in fluid communication with the air intake system and the gas turbine engine , the combustion inlet air path receiving the filtered air from the air filter inlet house and supplying the filtered air as combustion inlet air to an inlet of the gas turbine engine ; and a foreign object damage (FOD) screen in the combustion inlet air path between the air filter inlet house and the inlet of the gas turbine engine to prevent debris from entering the inlet of the gas turbine engine , characterised in that the FOD screen includes one or more mesh screens and an air sock placed over the one or more mesh screens , the one or more mesh screens enclosed in a frame structure having horizontally and vertically extending rails defining individual segments of sub-frame structures formed by intersections of the horizontally extending rails with the vertically extending rails, each individual segment of sub-frame structures enclosing portions of the one or more mesh screens , wherein a surface of each of the one or more mesh screens in the individual segments of sub-frame structures and the air sock placed over the one or more screens comprises an anti-icing coating to prevent ice formation thereon, the anti-icing coating applied to each of the one or more mesh screens in the individual segments of sub-frame structures and the air sock in locations where there is direct particle impact with particles flowing through the combustion inlet air path and locations without direct particle impact with the particles flowing through the combustion inlet air path. <EOS>