The present application relates to a fuel supply device for a gas turbine, which can supply a first fuel and a second fuel having a high combustion speed to a combustor of the gas turbine. In the present device, a first fuel supply line and a second fuel supply line are merged at a merging portion and are connected to the combustor via a mixing line. The second fuel supply line is provided with a first shutoff valve serving as a controlled object when the combustion state is switched from a single fuel combustion state to a mixed fuel combustion state, and a flow meter provided upstream of the first shutoff valve. The flow meter can output a detection value of a flow rate of the second fuel in order to calculate a mixing ratio of the first fuel and the second fuel for monitoring an operating state of the gas turbine.

An aircraft can comprise an engine, an environmental control system, an engine controller, and a plurality of sensors detecting engine or aircraft parameters. Engine or aircraft operation can be updated in real time based on input from the sensors, including airflow management or operation parameters.