Patent ID: 11920521
Assignee: GENERAL ELECTRIC COMPANY
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  B | IPC B  F

Claim 15:
16. A non-transitory computer readable medium comprising computer-executable instructions, which, when executed by one or more processors associated with a gas turbine engine, cause the one or more processors to:
determine, by executing a feedforward module, a first fuel flow demand based at least in part on a power demand rate associated with a load mechanically coupled with the gas turbine engine;
determine, by executing an aggressive control module, a second fuel flow demand based at least in part on i) a power turbine speed error associated with a power turbine of the gas turbine engine; and ii) a power turbine speed error rate derived from the power turbine speed error;
determine, by executing a power turbine governor module, a third fuel flow demand based at least in part on the power turbine speed error;
determine a composite fuel flow demand based at least in part on the first fuel flow demand, the second fuel flow demand, and the third fuel flow demand; and
control a fuel flow to the gas turbine engine based at least in part on the composite fuel flow demand.