Turbine engine including a steam system

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

• a fan including a plurality of fan blades that rotates to generate a volume of air;
• a nacelle that circumferentially surrounds the fan;
• a core turbine engine comprising:
• a compressor that compresses a portion of the volume of air to generate compressed air, the compressor including from ten stages to twelve stages and a compression ratio that is greater than 24:1 and less than or equal to 40:1;
• a combustor that combusts the compressed air and fuel to generate combustion gases;
• and
• a turbine including a shaft and having only one stage of turbine stator vanes and turbine rotor blades, the compressor, the combustor, and the turbine defining a core air flowpath, and the compressor being drivingly coupled to the shaft such that rotation of the turbine causes the compressor to rotate;
• one or more core exhaust nozzles extending radially through a downstream section of the nacelle and in fluid communication with the turbine;
• and
• a steam system that extracts water from the combustion gases, vaporizes the water to generate steam, and injects the steam into the core air flowpath to add mass flow to the combustion gases, wherein the combustion gases flow from the steam system and out of the turbine engine through the one or more core exhaust nozzles.