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AssigneeThe United States of America as represented by the Administrator of the National Aeronautics and Space Administration
InventorsJack E. Cornett, Andrew A. Saunders, Jr., Ira E. Marvin, Richard S. Beitler
Estimating the term…
An integrated control system for a gas turbine engine of the turbofan type receives signals from a plurality of engine sensors and from the engine operator and generates control signals therefrom. A first control signal regulates the fan exhaust nozzle area in order to control inlet throat Mach number to maintain a low level of engine noise. Additional control signals regulate fuel flow to control engine thrust and fan pitch to control fan speed. A plurality of schedules are utilized to maintain a predetermined relationship between the controlled parameters and a number of fixed and calculated limits can override the control signals to prevent unsatisfactory engine performance.
In a gas turbine engine of the turbofan type which includes a wall spaced apart from a core engine to define a bypass duct therebetween, said duct including an inlet and a variable area fan exhaust nozzle, a control system comprising:
A method of controlling the operation of a gas turbine engine of the turbofan type which includes a wall spaced apart from a core engine to define a bypass duct therebetween, said duct having an inlet and a variable area fan exhaust nozzle comprising the steps of:
Dependencies are inferred from the claim text.