Turbine engine including a gas path component having a hydrophobic coating

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

• a combustor located in a core air flow path to receive compressed air and fluidly coupled to both a fuel source and a steam source to receive fuel and steam, respectively, the fuel and steam 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 core shaft;
• a turbine located downstream of the combustor to receive the combustion gases and to rotate the turbine, the turbine being coupled to the core shaft to rotate the core shaft when the turbine rotates;
• and
• a steam system fluidly coupled to the combustor as the steam source to provide steam to the combustor, the steam system including:
• a hot gas path fluidly coupled to the combustor to receive the combustion gases and to route the combustion gases through the steam system;
• and
• a steam hot gas path component fluidly connected to the hot gas path, the steam hot gas path component including a plurality of combustion-gas passages, each combustion-gas passage of the plurality of combustion-gas passages being defined by a wall having a combustion-gas-facing surface facing the hot gas path, a portion of the plurality of combustion-gas passages being hydrophobic-coated combustion-gas passages with a hydrophobic coating formed on the combustion-gas-facing surface, and the remaining combustion-gas passages of the plurality of combustion-gas passages being uncoated combustion-gas passages that are free from the hydrophobic coating.