Gas turbine engine system
AssigneeROLLS-ROYCE plc
InventorsArnold C. Newton, John Sharp
Life of this patent
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Abstract
An aircraft mounted gas turbine engine system comprises a three shaft propulsive gas turbine engine having three electrical generators; each one respectively associated with one shaft of the engine. Two of the electrical generators are additionally configured so as to function as electric motors so as to facilitate power transfer between the engine shafts. One of the electric generators provides the primary source of electrical power for the aircraft, while the remaining electrical generators provide electrical power for the engine and back-up power for the aircraft.
Claims16
An aircraft mounted gas turbine engine system comprising a propulsive gas turbine engine having a core unit that includes compressor and turbine portions and a propulsive fan driven by said core unit, said engine including a plurality of electrical generators and a plurality of independent shafts with at least one of said shafts connected between a said turbine portion and a said compressor portion and one other of said shafts connected between another said turbine portion and another said compressor portion and with one of said shafts connected to said fan, each of said shafts independently driving one of said electrical generators, one of said electrical generators operationally constituting a primary source of electrical power for the aircraft carrying said engine.
Dependencies are inferred from the claim text.