| CPC F02C 6/18 (2013.01) [F02C 3/30 (2013.01); F01K 23/10 (2013.01); F02C 6/20 (2013.01)] | 20 Claims |
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1. 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 a fuel source, 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 shaft;
a turbine located downstream of the combustor to receive the combustion gases, the turbine being drivingly coupled to the shaft and rotated in response to receiving the combustion gases; and
a steam system including:
a boiler located downstream of the combustor, the boiler having water therein and being fluidly connected to the combustor to receive a first portion of the combustion gases from the combustor and to boil the water to generate steam;
a superheater fluidly connected to the boiler to receive a flow of the steam from the boiler, the superheater being located downstream of the combustor to receive a second portion of the combustion gases from the combustor and to heat the steam;
a steam dryer located downstream of the boiler and upstream of the superheater relative to the flow of the steam to remove entrained liquid water from the steam; and
a steam turbine fluidly coupled to the superheater to receive the steam from the superheater, the steam turbine being drivingly coupled to the shaft and rotated in response to receiving the steam.
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