Turbine engine including a gas path component having a hydrophobic coating

A turbine engine for an aircraft, the turbine engine comprising:

• an engine core including:
• a core air flow path for core air to flow therethrough;
• a high-pressure compressor located in the core air flow path to compress air, the high-pressure compressor having 10, 11, or 12 stages and a compression ratio greater than 20:1;
• a combustor located in the core air flow path to receive the compressed air and fluidly coupled to a fuel source to receive fuel, the fuel being injected into the combustor to mix with the compressed air to generate a fuel and air mixture, the fuel and air mixture being combusted in the combustor to generate combustion gases;
• a hot gas path routing the combustion gases through the turbine engine, the hot gas path being a portion of the core air flow path;
• and
• a high-pressure turbine fluidly connected to the hot gas path to receive the combustion gases and to cause the high-pressure turbine to rotate, the high-pressure turbine being coupled to the high-pressure compressor to rotate the high-pressure compressor when the high-pressure turbine rotates, the high-pressure turbine being a single stage including at least one turbine airfoil, the high-pressure turbine including a plurality of turbine blades, at least one turbine blade of the plurality of turbine blades including an airfoil having a cooling passage formed on an interior of the airfoil for cooling air to flow therethrough and a cooling-passage-facing surface facing the cooling passage;
• and
• a steam system including:
• a condenser located downstream of the combustor to condense water from the combustion gases and to generate an exhaust-water mixture;
• and
• a boiler fluidly coupled to the condenser to receive the water from the exhaust-water mixture and boil the water to generate steam, wherein the core air flow path is fluidly coupled to the boiler for the steam to be injected into the core air flow path to add mass flow to the core air,
• wherein the at least one turbine blade includes an interior hydrophobic coating formed on the cooling-passage-facing surface, reducing wetting of water vapor within the cooling air on the cooling-passage-facing surface.