A gas turbine engine comprises a plurality of fan rotors. A gas generator comprises at least one compressor rotor, at least one gas generator turbine rotor, a combustion section, and a fan drive turbine downstream of at least one gas generator turbine rotor. A shaft is configured to be driven by the fan drive turbine. The shaft engages gears to drive the plurality of fan rotors. A system controls the amount of power supplied to the plurality of fan rotors. A method of operating a gas turbine engine is also disclosed.
Gas turbine engine with distributed fans with drive control
06.03.2018
Patent
Elektronische Ressource
Englisch
GAS TURBINE ENGINE WITH DISTRIBUTED FANS DRIVEN ON ANGLED DRIVE SHAFT
Europäisches Patentamt | 2015
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