| CPC F02C 3/305 (2013.01) [F02K 3/077 (2013.01); F01D 25/32 (2013.01)] | 20 Claims |
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1. A turbine engine comprising:
a primary fan including a plurality of primary fan blades that rotates to increase a pressure of a volume of air;
a secondary air splitter positioned downstream of the primary fan to split the volume of air into bypass air and secondary air, the secondary air splitter defining a secondary air inlet;
a booster fan positioned downstream of the secondary air inlet, the booster fan including a plurality of booster fan blades that rotates to increase a pressure of the secondary air;
a core air splitter positioned downstream of the booster fan to split the secondary air into cooling air and core air;
a turbo-engine including:
a combustor that combusts compressed air and fuel to generate combustion gases;
a turbine including a turbine shaft, the primary fan coupled to the turbine shaft such that rotation of the turbine causes the primary fan to rotate; and
a core air flow path at least partially defined by the combustor and the turbine, the core air flowing into the core air flow path;
a nacelle that circumferentially surrounds the primary fan, the nacelle defining a bypass airflow passage between the nacelle and the turbo-engine, the bypass air flowing through the bypass airflow passage;
a cooling air duct defined radially between the core air flow path and the bypass airflow passage, the cooling air flowing into the cooling air duct; 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 flow path, the steam system including a condenser positioned in the cooling air duct to transfer heat from the combustion gases to the cooling air and to condense the water from the combustion gases.
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